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NASA Technical Memorandum 4155
An Experimental Investigation of
Thrust Vectoring Two-Dimensional
Covergent-Divergent Nozzles
Installed in a Twin-Engine Fighter
Model at High Angles of Attack
Francis J. Capone, Mary L. Mason,and Laurence D. Leavitt
Langley Research Center
Hampton, Virginia
National Aeronautics andSpace Administration
Office of Management
Scientific and TechnicalInformation Division
1990
Summary
This paper presents results from an investigation
to determine the thrust vectoring capability of sub-
scale, two-dimensional convergent-divergent exhaust
nozzles installed on a twin-engine general research
fighter model at angles of attack from -2 ° to 35 °.
Pitch thrust vectoring was accomplished by down-
ward rotation of nozzle upper and lower flaps. Theeffects of nozzle sidewall cutback were studied for
both unvectored and pitch-vectored nozzles. A single
cutback sidewall was employed for yaw thrust vector-
ing. This investigation was conducted in the Langley
16-Foot Transonic Tunnel at Mach numbers ranging
from 0 to 1.20. High-pressure air was used to sinl-
ulate the jet exhaust and provide values of nozzle
pressure ratio up to 9.Nozzle sidewall cutback caused little or no effect
on peak static nozzle performance for both unvec-
tored and pitch-vectored nozzles. Thrust-minus-drag
performance for the unvectored nozzle configurations
varied less than 1 percent at subsonic speeds, thus
showing the relative insensitivity of installed perfor-mance to nozzle sidewall cutback. At static condi-
tions, resultant pitch vector angle was always greater
than the geometric pitch vector angle for the three
configurations tested. The increment in either the
force or moment coefficient that resulted from pitch
or yaw vectoring remained essentially constant over
the entire angle-of-attack range for all Mach numbers
tested. Longitudinal control power was a function of
nozzle pressure ratio and Mach number. Powered
controls were very effective at low Mach numbers,but their effectiveness decreased as Mach number in-
creased because of a reduction in thrust. Longitudi-
nal control power from thrust vectoring was greaterthan that provided by aerodynamic controls at low
speeds. Negative yaw vector angles were generated at
underexpanded nozzle operating conditions, but pos-
itive yaw vector angles were found at overexpanded
nozzle operating conditions for a nozzle using a single
cutback sidewall to produce yaw thrust vectoring.
Introduction
The next generation of fighter aircraft will bea versatile class of vehicles designed for operation
over a wide range of flight and combat conditions.
Future fighter aircraft requirements will probably
include transonic and supersonic cruise capability,
short takeoff and landing (STOL) features, high turn
rates, and maneuvering at both conventional and
high angles of attack. Studies have shown that signif-
icant advantages in air combat are gained with the
ability to perform transient maneuvers at high an-
gles of attack including brief excursions into post-
stall conditions. (See refs. 1 to 5.) Current fighters
are somewhat limited in their angle-of-attack enve-
lope because inadequate aerodynamic control power
exists at high angles of attack.
Augmenting existing aircraft control systems with
multiaxis thrust vectoring could greatly enhance the
effectiveness of fighter aircraft and allow them to ex-
ploit a much-expanded angle-of-attack envelope. If
current flight capabilities are sufficient, augmenting
existing fighter aircraft control systems could allow
the designer the option of reducing empennage size,
thus reducing total airframe drag. In either case, im-
proved low-speed, high-angle-of-attack performance
and STOL capability are likely benefits of the use of
thrust vectoring (refs. 6 to 8).
A number of investigations conducted at both
static (wind-off) and forward speeds have verified the
effectiveness of multifunction nozzles for pitch thrust
vectoring. (For example, see refs. 9 to 14.) Morerecent studies have evaluated static and wind-on
effects of lateral or yaw thrust vectoring on installed
nozzle performance (refs. 9, 10, and 14 to 16).
This paper presents results from an investigation
to determine the thrust vectoring capability of sub-
scale, two-dimensional convergent-divergent exhaust
nozzles installed on a twin-engine general research
fighter model at angles of attack from -2 ° to 35 ° .
Pitch thrust vectoring was accomplished by down-
ward rotation of nozzle upper and lower flaps. Theeffects of nozzle sidewall cutback were studied for
both unvectored and pitch-vectored nozzles. A singlecutback sidewall was employed for yaw thrust vector-
ing. This investigation was conducted in the Langley
16-Foot Transonic Tunnel at Mach numbers ranging
from 0 to 1.20. High-pressure air was used to sim-
ulate the jet exhaust and provide values of nozzle
pressure ratio up to 9.
Symbols
All model longitudinal forces and moments are
referred to the stability axis system, and all lateralforces and moments are referred to the body axis
system. The model moment reference center waslocated 1.75 in. above the model centerline at fuselage
station 36.06 in. (FS 36.06) which corresponds to0.25_. A discussion of the data reduction procedure
and definitions of the aerodynamic force and moment
terms and the propulsion relationships are presented
in the appendix. Further details of the data reduction
and calibration procedures used herein can be found
in references 7 and 18. The symbols used in the
computer-generated tables are given in parentheses.
Ae
Anlax
Arab,1
Arab,2
Aseal, 1
Aseal,2
At
AR
b
bn
CD
C D,aft
CD,n
CD-F
CL
CL,aft
CL,n
CL,t
(CD)
(CDAFT)
(CDN)
(C(D-F))
(CL)
(CLAFT)
(CLN)
(CLT)
(CROLL)
nozzle exit area, in 2
maximum model cross-
sectional area, in 2
model cross-sectionalarea at FS 44.75 and48.25, in 2
model cross-sectional area
at FS 66.25, in2
cross-sectional area enclosed
by seal strip at FS 44.75and 48.25, in2
cross-sectional area enclosed
by seal strip at FS 66.25,in2
nozzle throat area, in 2
nozzle aspect ratio, ratioof nozzle throat width to
height
wing span, 40.00 in.
maximum nozzle width, in.
total aft-end drag coeffi-cient, CD =- CD-F atNPR = 1.0 (jet off)
afterbody drag coefficient
nozzle drag coefficient
drag-minus-thrust coeffi-
cient, Drag - Thrustq_c S
total aft-end aerodynamic
lift coefficient, CL -- CL,t at
NPR = 1.0 (jet off)
afterbody lift coefficient
nozzle lift coefficient
total aft-end lift coefficient,including thrust component,Lift
lift effectiveness due to
thrust vectoring, per degree
total aft-end rolling-moment
coefficient, C/ = C/, t atNPR - 1.0 (jet off)
el,t
Cm
era,aft
6771, Tl
Cm,t
CT-n
Gin8 v
Vn
T_t
%
cr
cr, t
D
DI
F
FA
F A ,Mbal
(CROLLT)
(CM)
(CMAFT)
(CMN)
(CMT)
(CN)
(CNT)
(CY)
(CYT)
total aft-end rolling-momentcoefficient including thrustcomponent, Rolling moment
qoc Sb
total aft-end aerodynamicpitching-moment coeffi-cient, Cm = Cm,t atNPR = 1.0 (jet off)
afterbody pitching-momentcoefficient
nozzle pitching-momentcoefficient
total aft-end pitching-moment coefficient in-
cluding thrust component,Pitching moment
qcc 8"5
longitudinal control power,per degree
longitudinal control powerdue to pitch vectoring, perdegree
total aft-end yawing mo-ment, Cn = Cn,t atNPR = 1.0 (jet off)
total aft-end yawing mo-ment including thrust eom-ponent_ Yawing moment
qoc Sb
pressure coefficient,(P - Poc)/qoc
total aft-end side-force
coefficient, Cy =- Cy, t atNPR = 1.0 (jet off)
total aft-end side-force
coefficient including thrustcoefficient, Side force
wing mean geometric chord,17.42 in.
drag, lbf
friction drag, lbf
thrust along stability axis,lbf
total aft-end axial force, lbf
axial force measured bymain balance, lbf
A _mom
FA,Sbal
/Waft
Fc
tq
FN
Fs
g
L
Lj
Lt
M
NPR
(NPR)des
P
pa
Pes,1
(MACH)
(NPR)
momentum tare axial force
due to bellows, lbf
axial force measured byafterbody shell balance, lbf
afterbody axial force, lb
resultant gross thrust,
v/F/+ F 2 + F 2, lbf
ideal isentropicgross thrust,
[1_Wp _ 9,2 _-1
(N_) ("/-1)/3'] } 1/2 , lbf
measured thrust along bodyaxis, lbf
measured jet normal force,lbf
measured jet side force, lbf
gravitational constant,
32.174 ft/sec 2
length from nozzle attach-ment station (FS 66.30) tonozzle exit, used in coordi-nate system of figure 6(a)
length from moment ref-erence center to nozzle
throat, in.
length from moment refer-ence center to quarter-chordof horizontal tail mean
geometric chord, in.
length from nozzle throatto nozzle exit, used incoordinate system offigure 6(b), in.
free-stream Math number
nozzle pressure ratio,
Pt,j/P_c or Pt,j/Pa
nozzle pressure ratio re-quired for fully expandedflow
local static pressure, psi
ambient pressure, psi
average static pressure atexternal seal at FS 44.75,psi
Pes,2
Pes 3
Pt,j
BOC
q_C,
R
S
St
Tt,j
V
wi
Wp
X
x
Y
average static pressure atexternal seal at FS 48.25,
psi
average static pressure atexternal seal at FS 66.25,psi
average internal staticpressure, psi
average jet total pressure,psi
free-stream static pressure,psi
free-stream dynamic pres-sure, psi
gas constant, 1716 ft2/see2-°R
wing reference area,664.4 in 2
horizontal tail area, in 2
average jet total tempera-ture, °R
volume coefficient (see theappendix)
ideal weight-flow rate,
lbf/sec
measured weight-flow rate,lbf/sec
axial distance measuredfrom nozzle attachment sta-
tion (FS 66.30), positivedownstream, used in coor-dinate system of figure 6(a),in.
axial distance measured
from nozzle throat, positivedownstream, used in coor-dinate system of figure 6(b),in.
lateral distance measured
from model centerline,
positive to left (outboard)looking downstream, usedin coordinate system offigure 6(a), in.
3
Y
c_
_p
(ALPHA)
Abbreviations:
A/B
BL
C-D
FS
STOL
WL
2-D
lateral distance measured
from nozzle centerline,
positive to left (outboard)looking downstream, used
in coordinate system of
figure 6(b), in.
angle of attack, deg
ratio of specific heats,1.3997 for air
resultant pitch vector angle,
tan -1 -_j, deg
geometric pitch vector
angle measured from nozzle
centerline, positive for
downward deflection angles,deg
resultant yaw vector angle,
t an- 1 _._, deg
afterburning
butt line, in.
convergent-divergent
fuselage station (axial
location described bydistance in inches from
model nose)
short takeoff and landing
waterline, in.
two-dimensional
Apparatus and Procedure
Wind Tunnel
This investigation was conducted in the Lang-
ley 16-Foot Transonic Tunnel, a single-return atmo-
spheric wind tunnel with a slotted octagonal test
section and continuous air exchange. The wind tun-
nel has variable airspeeds up to a Mach number of
1.30. Test-section plenum suction is used for speeds
above a Mach number of 1.05. A complete descrip-
tion of this facility and operating characteristics canbe found in reference 17.
Model and Support System
Details of the general research twin-engine fighter
model and wingtip-mounted support system used in
4
this investigation are presented in figure 1. A pho-
tograph of the model and support system installed
in the Langley 16-Foot Transonic Tunnel is shown in
figure 2. A sketch of the wing planform geometry is
presented in figure 3.
The wingtip model support system shown in
figure 1 consisted of three major portions: the
twin support booms, the forebody (nose), and the
wing/centerbody. These pieces made up the non-
metric portion (that portion of the model not
mounted on force balance) of the twin-engine fighter
model. The fuselage centerbody was essentially rect-angular in cross section and had a constant width
and height of 10.00 in. and 5.00 in., respectively.The four corners were rounded by a radius of 1.00 in.
The maximum cross-sectional area of the centerbody(fuselage) was 49.14 in 2. The support system fore-
body (or nose) was typical of a powered model in that
the inlets were faired over. The wings were mounted
above the model centerline in a high position that
is typical of many current fighter designs. The wing
had a 45 ° leading-edge sweep, a taper ratio of 0.5,
an aspect ratio of 2.4, and a cranked trailing edge(fig. 3). The NACA 64-series airfoil had an airfoil
thickness ratio of 0.067 near the wing root. From BL
11.00 to the support booms, however, wing thicknessratio increased from 0.077 to 0.10 to provide ade-
quate structural support for the model and to permit
the transfer of compressed air from the booms to the
model propulsion system.
The wingtip support system has the unique fea-
ture of being able to rotate the wing with respect tothe support booms. This allows testing of models to
high angles of attack while keeping the model near
the tunnel centerline. A detailed description of the
wingtip support system is given in reference 17.
The metric portion of the model aft of FS 44.75,
supported by the main force balance, consisted of
the internal propulsion system, afterbody, tails, and
nozzles. The afterbody lines were chosen to provide a
length of constant cross section aft of the nonmetric
centerbody and to enclose the force balance and
jet simulation system while fairing smoothly down-
stream into the closely spaced nozzles. The afterbodyshell from FS 48.25 to 66.25 was attached to an af-
terbody force balance that was attached to the main
force balance (fig. 1). The main force balance in turn
was grounded to the nonmetric wing/centerbody sec-
tion. The nozzles were attached directly to themain force balance through the propulsion system
piping. Three clearance gaps (metric breaks) wereprovided between the nonmetric and individual met-
ric portions (afterbody and nozzles) of the model at
FS 44.75, 48.25, and 66.25 to prevent fouling of the
components upon each other. A flexible plastic strip
insertedinto circumferentiallymachinedgroovesineachcomponentimpededflowinto or out of the in-ternalmodelcavity(fig.1).
In this report, that sectionof the modelaft ofFS48.25is referredto asthe total aft end(whichincludesafterbodyand nozzles). That sectionofthe modelfromFS 48.25to 66.25is referredto asthe afterbody,and that sectionaft of FS 66.25isconsideredthe nozzles.An adjustmentto the dragresultsof themainbalancewasmadefor thesectionof the model from FS 44.75to 48.25. (Seetheappendix.)
Twin-Jet Propulsion Simulation System
The twin-jet propulsion simulation system is
shown in figure 1. An external high-pressure air sys-
tem provided a continuous flow of clean, dry air at a
controlled temperature of about 70°F at the nozzles.
This high-pressure air was brought into the wind-
tunnel main support strut where it was divided into
two separate flows and passed through remotely op-erated flow-control valves. These valves were used to
balance the total pressure in each nozzle.
The divided compressed airflows were piped
through the wingtip support booms, through the
wings, and into the flow-transfer (bellows) assem-
blies (fig. 1). A sketch of a single flow-transfer bel-
lows assembly is shown in figure 4. The air in each
supply pipe was discharged perpendicularly to the
model axis through six sonic nozzles equally spacedaround the supply pipe. This method was designed
to minimize any transfer of axial momentum as the
air passed from the nonmetric portion to the met-
ric portion of the model. Two flexible metal bel-lows were used as seals and served to compensate for
the axial forces caused by pressurization. The cav-
ity between the supply pipe and bellows was vented
to model internal pressure. The airflow then passed
through the tail pipes into the transition sections,
through choke plates (30 percent of the tail pipe open
area), to the instrumentation or charging sections,and then to the exhaust nozzles. (See fig. 1.)
Exhaust Nozzles
The two-dimensional convergent-divergent (2-D
C-D) nozzle is a nonaxisymmetric exhaust system inwhich a symmetric contraction and expansion pro-
cess takes place internally in the vertical plane. Basic
nozzle components consist of upper and lower flaps
to regulate the contraction and expansion processand flat nozzle sidewalls to contain the flow laterally.
The flap inner-surface geometry (on full-scale hard-
ware) can be varied or altered by actuators so that
(1) the engine power setting can be changed by vary-ing the throat height and (2) the expansion surface
angle (the flat surface downstream of the throat) can
be varied for optimum expansion of the exhaust flow
(ref. 19). The 2-D C-D nozzle can be designed to vec-tor the exhaust flow up or down (in the pitch plane)
by rotating the upper and lower flaps independently.
The subscale 2-D C-D nozzle models tested during
this investigation are shown in figure 5. These noz-
zles are fixed-geometry representations of a variable-
geometry nozzle at dry power and partial afterburn-
ing (A/B) power settings. The nozzle models were
sized to the twin-engine wingtip-supported propul-sion simulator by selecting values of the ratio of to-
tal nozzle throat area to maximum fuselage cross-
sectional area (2At/Amax) that were representative
of current twin-engine high-performance aircraft in-stallations. The values of nozzle internal expansion
ratio selected for testing were based on typical cur-
rent, full-scale, mixed-flow turbofan cycles. A sum-
mary of important geometric parameters is given in
the following table:
Power
setting At, in. Ae/At 2At/Amax
Dry 2.69 1.16 0.11
A/B 3.92 1.24 .16
AR (NPR)des3.45 3.46
2.39 4.17
Various combinations of nozzle flap and sidewall ge-
ometry were examined as seen in figure 5. Three ba-
sic upper and lower flap arrangements were tested:unvectored flaps, pitch-vectored A/B flaps, and un-
vectored dry power flaps. The pitch vectoring wasproduced by a simple 15 ° downward rotation of the
unvectored A/B nozzle divergent flaps. The sidewall
geometry variations used with each of the upper and
lower flap arrangements are indicated in figure 5(b).
The A/B sidewalls were designed to fair smoothlywith the external lines of the A/B flaps. When paired
with the dry power flaps, the A/B sidewalls provide
small external flow fences. Conversely, the dry power
sidewall (designed to fair with the dry power flaps)allows some internal flow ventilation when combined
with the A/B flaps.
The effects of sidewall cutback were investigated
on both the unvectored and pitch-vectored A/B flaps
as seen in figure 5(b). The baseline or 100-percent
A/B sidewall provided full exhaust flow containmentover the entire divergent flap of the unvectored noz-
zle. The 50- and 25-percent sidewall cutbacks pro-
vided one-half and one-quarter containment, respec-
tively, of the unvectored A/B divergent flap length.
5
Becausesidewallbaseareaswere held constant,sidewallboattailanglevariedwith sidewallcutbackasshownin theviewlabeled"Topview."
Thesidewallvariationsdiscussedin thepreviousparagraphsreferonly to the outboardsidewallofeachnozzle.For the closelyspacedtwin-nozzlear-rangementofthepresentinvestigation,acommonin-boardsidewall(splitterplate)ismorepracticalthanindividualsidewalls.Thesplitterplategeometrywasconstantthroughoutthe entireinvestigation.ThissplitterplaterepresentedtwobaselineA/B sidewalls(with100-percentcontainment)locatedbacktoback.Thesplitter plateis identifiedin the sketchof fig-ure5(a)andthephotographof figure5(c).
Yawvectoringwasprovidedby an asymmetriccombinationof sidewalllengthson the A/B nozzleflaps.A 100-percentA/B sidewallwaslocatedout-boardontheleft nozzle,anda 25-percentA/B side-wallwaslocatedoutboardon theright nozzle.Thiscombinationof sidewallcutbackrepresenteda yaw-vectoringconceptcalledthetranslatingsidewallcon-cept. In a full-scaleapplication,a singlesidewallwouldtranslate,whereasthe oppositesidewallre-mainedin the full containmentposition. This lat-eral asymmetrywouldproducea yaw vectoran-gle whosemagnitudecanbevariedby varyingtheamountof sidewalltranslation.A moredetaileddis-cussionof thisyaw-vectoringconceptiscontainedinreference14.
Instrumentation
Forces and moments oil the metric portions of themodel were measured by two six-component strain
gauge balances. The main balance measured forces
and moments resulting from nozzle gross thrust and
the external flow field over that portion of the model
aft of FS 44.75. The afterbody balance measured
forces and moments resulting from the external flow
field over the afterbody from FS 48.25 to 66.25. This
twin balance arrangement permits the separation of
model component forces for data analysis.
External static pressures were measured at eight
points in the seal gap at the first metric break
(FS 44.75). All orifices were located on the non-
metric centerbody and spaced symmetrically aboutthe model perimeter. An additional five orifices
positioned about the right side of the model mea-sured seal gap pressures at the second metric break
(FS 48.25). The third and final set of seal pressures
was measured by two pairs of surface taps, each an
equal distance fore and aft of the third metric break
(FS 66.25).
In addition to these external pressures, two in-ternal pressures were measured at each metric seal.
These pressure measurements were then used to cor-
rect measured axial force and pitching moment for
pressure area tares as discussed in the appendix.Chamber pressure measurements made in each
supply pipe, upstream of the six sonic nozzles (fig. 4),were used to compute mass-flow rates for each noz-
zle and were also used to compute tare forces. In-
strumentation in each charging section consisted of
a stagnation-temperature probe and a total-pressure
rake. Each rake contained four total-pressure probes.(See fig. 5.) Nozzle total pressure was determinedfrom these measurements.
External and internal static pressures were mea-
sured on the two A/B power nozzles. The orifice lo-
cations are shown in figure 6. External pressures were
measured on the right nozzle (looking upstream).The external orifices were arranged in three rows
along the top surface of the convergent and diver-
gent flaps of the nozzle. Internal static pressures were
measured on the left nozzle (looking upstream). Theinternal orifices were located only along the divergent
flap, starting at the nozzle throat. A single row of ori-
fices was placed along the centerline of the top flap,
and three rows of orifices were placed along the sur-face of the bottom flap. All pressures were measured
with individual pressure transducers. Data obtained
during each tunnel run were recorded on magnetic
tape. Typically, for each data point, 50 frames of
data were taken over a period of 5 sec and the aver-
age was used for computational purposes.
Tests
This investigation was conducted in the Langley16-Foot Transonic Tunnel at Mach numbers of 0,
0.15, 0.60, 0.90, and 1.20 and at angles of attack from
-2 ° to 35 ° . The nozzle pressure ratio varied from
1.0 (jet off) to 9.0 depending upon Mach number.
Most model configurations were tested at angles of
attack from -2 ° to 18 ° . Selected configurations were
subsequently tested over an angle-of-attack range
from about 16.6 ° to 35 ° . This was accomplishedby presetting wing incidence through rotation of the
wings with respect to the wing support booms. Basic
data were obtained by varying nozzle pressure ratio
at an angle of attack of 0° and by varying angle
of attack at jet off and at a fixed (different for
each Mach number) nozzle pressure ratio. The fixednozzle pressure ratio tested at each Mach number
represented a typical operating pressure ratio for a
turbofan engine at that Mach number. The Reynoldsnumber based on the wing mean aerodynamic chordvaried from 4.4 x 106 to 5.28 × 106.
All tests were conducted with 0.10-in-wide
boundary-layer transition strips consisting of No. 120silicon carbide grit sparsely distributed in a thin film
of lacquer.A singlestrip waslocated1.00in. fromthe tip of the forebodynose.Additional transitionstripswereplacedonbothupperandlowersurfacesof thewingsat 5percentof theroot chordto 10per-centof thetip chord.
Presentation of Results
The results of this investigation are presented
in both tabular and plotted form. Table 1 is anindex to the results contained in tables 2 to 13.
The computer symbols appearing in these tables are
defined in the Symbols section of the paper with theircorresponding mathematical symbols. Only data for
the A/B powered nozzle are presented in plotted formin this report. However, all data are tabulated.
Discussion
Pitch Thrust Vectoring
Static performance. The effect of cutback side-
walls on nozzle static performance for the afterburner
power nozzles with geometric pitch vector angles
of 0 ° and 15 ° is presented in figures 7 and 8, re-spectively. Static nozzle performance is presented
as internal thrust ratio F/Fi, internal gross thrust
ratio FG/Fi, resultant pitch vector angle @, and
nozzle discharge coefficient Wp/Wi. Both cutback
sidewall nozzle configurations at 6v,p = 0° had higherthrust performance than the full sidewall configura-
tion at overexpanded conditions (NPR less than de-
sign NPR). Similar effects were found for the dry
power nozzle (ref. 20).
Peak nozzle performance occurred between nozzle
pressure ratios of 4 and 5. Typically, the peak nozzle
performance is obtained at the jet nozzle pressure
ratio required for fully expanded flow (the design
pressure ratio), which for the current nozzles is 4.17.There is no effect of sidewall cutback on internal gross
thrust ratio at peak nozzle performance conditions
(fig. 7). Thus, there is no indication that cutbacksidewalls caused a decrease in the effective expansion
ratio of the nozzle that would have resulted in peak
performance occurring at a lower nozzle pressure
ratio. Earlier investigations showed that a reductionin effective nozzle expansion ratio would be expected
with cutback sidewalls (refs. 12 and 20),The effect of cutback sidewalls on nozzle per-
formance for the nozzle with a pitch vector an-
gle of 15 ° is presented in figure 8. As was the
case for the unvectored nozzle, both cutback side-
wall nozzle configurations had a higher thrust per-formance than the nozzle with full sidewalls at over-
expanded conditions. Differences in peak nozzle
performance were less than 1 percent of the internal
gross thrust ratio. A comparison between the unvec-
tored and vectored nozzles shows similar gross thrust
ratios indicating little or no losses due to flow turn-
ing. The pitch-vectoring concept was very effective
in that resultant pitch vector angles were produced
that were greater than the geometric pitch angle of
15 ° at all nozzle pressure ratios tested. Such large
pitch vector angles, typical of pitch vectoring by dif-
ferential flap deflection (refs. 9 to 13), are caused in
part by local overexpansion at the nozzle throat onthe lower flaps of the nozzle. This very localized re-
gion of overexpanded flow forms immediately down-stream of the throat and forces the exhaust flow to
overturn before expanding onto the lower flap.
Basic aeropropulsive performance. The effect
of cutback sidewalls on basic aeropropulsive per-
formance with the nozzle at zero pitch vector an-
gle is presented in figure 9. The variation of the
aeropropulsive parameter (F - D)/F i and total aft-
end drag coefficient with nozzle pressure ratio is
presented for Mach numbers from 0.60 to 1.20.
As expected, because of increased drag, the nero-
propulsive performance of all configurations de-
creased with increasing Mach number. Consistenttrends with a cutback sidewall are not evident at
subsonic Mach numbers (fig. 9(a)). However, dif-ferences in aeropropulsive performance of less than 1
percent occurred at typical operational pressure ra-
tios. At M = 1.20, the nozzle configuration with the
100-percent sidewalls had the highest aeropropulsive
performance over the entire NPR range tested.
At subsonic speeds, there are no consistent trends
in aft-end drag as the nozzle sidewall is cut back
(fig. 9(b)). However, the configuration with the 100-percent sidewalls had the lowest jet-off drag coeffi-
cient at all Mach numbers tested, and the configu-
ration with the 25-percent sidewalls had the highest
drag. This probably results from the cutback side-
walls having a steeper boattail angle than that of the
full sidewall (fig. 5(b)).
Pitch vectoring at forward speeds. The effect
of cutback sidewalls on total longitudinal character-
istics for the nozzles with geometric pitch vector an-
gles of 0 ° and 15 ° at a = 0° is presented in figures 10
and 11, respectively. Generally, the effect of cut-
back sidewalls was small. Similar results (not shown
in the figure) were found at c_ = 20 ° between the
100-percent and 25-percent sidewalls at M = 0.15
and 0.60. (See tables 2 and 4.)
The increment in C L or Cm between 6v,p = 0°
(fig. 10) and 6v,p = 15 ° (fig. 11) at jet-off conditions(NPR = 1.0) results from the aerodynamic flap effect
7
of the deflectednozzledivergentflaps. (Seefig. 5.)As nozzlepressureratio increases,C L increases andCm becomes more negative for the pitch-vectored
configuration. The increase in lift coefficient with
increasing NPR is due primarily to the jet lift compo-
nent of the nozzle gross thrust and some jet-inducedlift. Jet-induced lift can be determined from the to-
tal aft-end aerodynamic lift coefficient CL presented
in tables 7 to 9. For this configuration with the
100-percent sidewalls, jet-induced lift varied from
about 20 to 30 percent of the total aft-end aero-
dynamic lift coefficient C L at Mach numbers from0.60 to 1.20. Similar results were obtained inreference 13.
The drag-minus-thrust coefficient varies nearly
linearly with nozzle pressure ratio regardless of pitch
thrust vector angle. The differences between CD_ F
for _v,p = 0° and CD_ F for _v,p = 15 ° result both
from thrust losses caused by turning the exhaust vec-
tor away from the axial direction and from generally
higher drag on the 5v,p = 15 ° configuration. (Seetable 7.) Increasing the magnitude of negative num-
bers for CD-F indicates improved performance from
either higher thrust or lower drag.
The effect of angle of attack on the total aft-
end longitudinal aerodynamic characteristics for thenozzle with 100-percent and 25-percent sidewalls is
presented in figures 12 and 13, respectively. Theincrement in lift or pitching-moment coefficient that
results from changing the nozzle pitch vector angle
from 0 ° to 15 °, at either jet-off or jet-on conditions,
remains essentially constant over the entire angle-
of-attack range for all Mach numbers tested. Thus,
there is also no effect of pitch thrust vectoring on lift-
curve slope and longitudinal stability characteristics.Similar results are reported in references 9 and 10.
Longitudinal control power. Longitudinal control
power and lift effectiveness due to thrust vectoring
are presented in figure 14. These parameters at a
constant Mach number are only a function of nozzle
pressure ratio because the aerodynamic increments
that resulted from thrust vectoring were independent
of angle of attack. The decrease in control power thatoccurs as Mach number increases is the result of a
decrease in thrust (at constant NPR). The decrease
in thrust is caused primarily by the decrease in free-
stream static pressure as Mach number increases and,
to a lesser extent, by free-stream dynamic pressureeffects.
A comparison of longitudinal control power Cm_from powered and aerodynamic controls is presentedin figure 15 as a function of Mach number at _ =
0 °. Longitudinal control power from pitch vectoringwas obtained for each Mach number shown at a
typical operating pressure ratio. These operating
pressure ratios are indicated in the keys of figure 12.
Longitudinal control power from pitch vectoring 2-D
C-D nozzles on an F-18 aircraft model (ref. 13)
and a supersonic cruise fighter (ref. 10) is shownin figure 15. Longitudinal control power generated
by the horizontal tail for the current configuration
(ref. 21), for the F-18 aircraft model (ref. 13), and by
a canard (ref. 10) is also presented in this figure. Note
that symbols are used to distinguish longitudinal
control power from pitch vectoring and that lines areused to denote aerodynamic controls.
At low speed, pitch vectoring provided a signif-icant increase in longitudinal control power when
compared with the horizontal tail (fig. 15). Simi-lar results for the other configurations are presented
in reference 9. The decrease in value of the pow-
ered controls with increasing Mach number is caused
by the decrease in thrust discussed previously. Be-
cause aerodynamic controls are usually sized for low
speed, they are generally more effective than is re-
quired at high speeds. Thus, thrust vectoring could
be used to augment the control power provided by
aerodynamic controls, particularly at low speeds. For
an aircraft design utilizing pitch thrust vectoring to
augment aircraft control, the size of the aerodynamicsurfaces could be reduced, and this reduction would
likely reduce the drag.
Yaw Thrust Vectoring
Static performance. The effect of yaw thrust vec-
toring utilizing asymmetric sidewall cutback (trans-
lating sidewall concept) at static conditions is pre-sented in figure 16. This yaw-vectoring concept
produced rather small (less than 3 ° ) values of re-
sultant yaw vector angles. At overexpanded nozzle
operating conditions (NPR < (NPR)des), the mea-sured yaw vector angles were positive; at under-
expanded nozzle operating conditions (NPR > 4.2),the yaw vector angles were negative. This effect of
thrust direction varying with pressure ratio is com-
mon in nonaxisymmetric nozzles whenever one flapis longer than the other relative to the exhaust flow
centerline. It occurs for both unvectored and vec-
tored single-expansion-ramp nozzles (see, for exam-
ple, refs. 13 and 22) and some vectored 2-D C-D noz-
zles where rotation of the individual flaps takes place
about axes near the throat. This type of nozzle ge-
ometry presents expansion surfaces of unequal lengthfor the flow to work against; thus, one side of the
exhaust flow is contained longer by a flap (in this in-vestigation, by the inboard sidewall) while the other
side of the exhaust flow is unbounded. The change
in the direction of the resultant yaw vector angles
as nozzle operation changes from overexpanded to
underexpandedindicatesthat the translatingside-wall conceptmay not be feasiblein generatingdirectionalcontrolat transientengineoperatingcon-ditions.This trendin yawvectoranglewith increas-ing NPRwasreportedasa resultof anearlierstaticstudy (ref. 15). However,the magnitudeof the re-sultantyawanglesis sosmall(seefig. 16)that littleusefuldirectionalcontrolcouldbeprovidedovertherangeof NPR'stested.Largeryawvectoranglesathighernozzlepressureratioswouldresultfromtrans-latingthesidewallupto orpastthenozzlethroat,butsuchsidewalltranslationwouldprobablydecreaseFG/F i. (See ref. 15.)
Yaw vectoring at forward speeds. The effect
of yaw thrust vectoring on the total aft-end lateral
aerodynamic characteristics is presented in figures 17and 18. The variation of the lateral characteristics
with NPR at c_ = 0 ° is shown in figure 17, whereas
the effect of angle of attack with jet off and constantNPR is shown in figure 18.
The variations in wind-on lateral characteristics
with NPR shown in figure 17 would be expectedfrom the static results discussed previously. (See
fig. 16.) The changes in direction of both Cn,t and
Cy, t are caused by the change in directions of 6y asthe nozzle operation changes from overexpanded to
underexpanded conditions. Thus, as discussed ear-
lier, yaw vectoring by truncated sidewalls may notbe feasible in producing positive yaw control over
the operational NPR range without further nozzle
geometry variations. As shown in figure 18, yawingmoment and the increment in Cn resulting from side-
wall translation were essentially independent of angle
of attack. The insensitivity of the Cn increment to
is identical to the results discussed previously for
pitch thrust vectoring on the longitudinal character-istics.
Internal Static Pressure Distributions
Internal static pressure distributions for the A/B
power nozzle with 100-percent sidewalls and 6v,p =
0° are presented in figure 19. As shown in fig-
ure 6(b), pressures were measured along the center-
line of the top and bottom divergent flap as well asoutboard and inboard locations on the bottom di-
vergent flap. In general, the measured internal static
pressure distributions are similar to those measuredin conventional round nozzles. For NPR = 2.0 at
M = 0, for example, the static pressures on the noz-
zle (fig. 19(a)) show a typical sudden pressure riseacross the exhaust-flow normal shock. As expected,there was little or no effect of external flow on the
internal pressure distributions at constant NPR.
The effect of nozzle pressure ratio on the internal
static distributions for the A/B power nozzle with
the 100-percent sidewalls and 6v,p = 15 ° is presented
in figure 20. The results indicate a highly inclinedthroat at static conditions as the flow becomes sonic
(P/Pt,j = 0.528) on the top flap at x/1 = 0.67. Thereis little or no effect of Mach number on these in-
ternal static pressure distributions at constant NPR
(fig. 20).The effect of 50- and 25-percent-cutback sidewalls
on internal nozzle pressure characteristics is shown
in figures 21 and 22, respectively. As shown, the ini-
tial 50-percent-cutback sidewall produces flow sepa-
ration along the outboard portion of the bottom flap
(fig. 21(a)). Additional truncation of the sidewall
enlarges the separation region and begins to affectthe nozzle centerline pressures along the bottom flap
(fig. 22(a)). As would be expected, the separated re-
gion on the nozzle flap decreases as nozzle pressureratio is increased. Similar effects due to cutback side-
walls would be expected to occur for the unvectored
nozzle and are typical for this type of nozzle (refs. 20
and 22). There was little or no effect of external
flow on the internal static pressure distribution atconstant NPR.
External Static Pressure Distributions
Afterbody/nozzle pressure distributions for the
model with a nozzle pitch vector angle of 0 ° and 100-
percent sidewalls are presented in figure 23. Pres-
sures were measured only on the top surface of the
afterbody/nozzle as shown in figure 6(a). These pres-sure distributions show typical results of a large ex-
pansion at the start of the afterbody boattail and a
recompression along the afterbody and nozzle. At
subsonic speeds, pressure recovery to positive values
of pressure coefficient on the nozzle with the 100-percent sidewalls (fig. 23) can produce negative val-
ues of nozzle drag as previously reported in refer-
ence 23 for the configuration with the nozzle in the
dry power mode. Figures 24 and 25 present similar
afterbody/nozzle pressure distributions for the noz-zles with 50- and 25-percent-cutback sidewalls and
show essentially no effect of cutback sidewall.
The effect of nozzle pressure ratio on afterbody/
nozzle pressure distributions for the model with a
nozzle pitch vector angle of 15 ° and 100-percent side-
walls is presented in figure 26. Thrust vectoring re-duces the recompression of the flow on the afterbody/
nozzle upper surfaces. In general, vectoring tends toincrease pressures on the lower surface of the config-
uration which generally results in some induced lift
being generated.The effect of cutback sidewall on the afterbody/
nozzle pressure distributions is presented in figures 27
to 30 for the pitch-vectored nozzle. At NPR < 3.5,
pressuresaremorepositiveasthe nozzlesidewallsarecut back,whereasat NPR= 6.0,pressuresaremorenegative. The largesteffectof the cutbacksidewalloccursontheoutboardportionofthesurfaceof the afterbody/nozzle.As nozzlepressureratioincreases,jet entrainmenteffectsprobablydominatethe flow field and morenegativepressuresresultfrom the pumpingactionof the vectoredexhaust.However,there is probablya pressurizationof thelowersurfaceundertheseconditionsbecausecutbacksidewallshad little or no effecton the afterbodyforcesandmoments(fig. 11).
Conclusions
An investigation has been conducted in the Lang-
ley 16-Foot Transonic Tunnel to determine the thrust
vectoring capability of two-dimensional convergent-
divergent nozzles installed on a twin-engine general
research fighter model. Pitch vectoring was accom-
plished by differential deflection of the nozzle upper
and lower divergent flaps. The effects of nozzle side-wall cutback were studied for both unvectored and
pitch-vectored nozzles. A single cutback sidewall was
employed for yaw thrust vectoring. This investiga-
tion was conducted at Mach numbers from 0 to 1.20,
at angles of attack from -2 ° to 35 ° , and at nozzle
pressure ratios up to 9. An analysis of the results of
this investigation indicates the following conclusions:
1. Nozzle sidewall cutback caused little or no
effect on peak static nozzle performance for both
unvectored and pitch-vectored nozzles.
2. Thrust-minus-drag performance for the unvec-
tored nozzle configurations varied less than 1 percent
at subsonic speeds, thus showing the relative insen-
sitivity of installed performance to nozzle sidewallcutback.
3. At static conditions, resultant pitch vector an-
gle was always greater than the geometric pitch vec-
tor angle.4. The increment in either the force or moment
coefficient that resulted from pitch or yaw vectoring
remained essentially constant over the entire angle-
of-attack range for all Mach numbers tested.
5. Longitudinal control power was a function of
nozzle pressure ratio and Mach number. Powered
controls were very effective at low Mach numbers,but their effectiveness decreased as Mach number
increased because of a reduction in thrust.
6. Longitudinal control power from thrust vector-
ing was greater than that provided by aerodynamic
controls at low speeds.
7. The yaw vectoring configuration tested was in-
effective at producing yaw vectoring at nozzle pres-sure ratios typical for operation at subsonic Mach
numbers. Negative yaw vector angles were gener-ated at underexpanded nozzle operating conditions,
but positive yaw vector angles were found at over-
expanded nozzle operating conditions for a nozzle us-
ing a single cutback sidewall to produce yaw thrust
vectoring.
NASA Langley Research CenterHampton, VA 23665-5225December 5, 1989
10
Appendix relationship:
Data Reduction and Calibration Procedure
Calibration Procedure
The main balance measured the combined forces
and moments due to nozzle gross thrust and theexternal flow field of that portion of the model aft of
FS 44.75. The afterbody balance measured the forcesand moments due to the external flow field exerted
over the afterbody between FS 48.25 and 66.25.
Force and moment interactions exist between the
bellows-flow transfer system (fig. 4) and the mainforce balance because the eenterline of this balance
is below the jet centerline (fig. 1). Consequently,
single and combined loadings of normal force, axial
force, and pitching moment were made with andwithout the jets operating with Stratford calibration
nozzles (ref. 17). These calibrations are performedwith the jets operating because this condition gives
a more realistic effect of pressurizing the bellows
than does capping off the nozzles and pressurizing
the flow system. Thus, in addition to the usual
balance-interaction corrections applied for a single
force balance under combined loads, another set
of interactions was applied to the data from this
investigation to account for the combined loadingeffect of the main balance with the bellows system.
These calibrations were performed over a range ofexpected normal forces and pitching moments. Note
that this procedure is not necessary for the afterbody
balance because the balance is not bridged by the
flow system.
Data Corrections
In order to achieve desired axial-force terms, the
axial forces measured by both force balances must
also be corrected for pressure-area tare forces acting
on the model, and the main balance must be cor-
rected for momentum tare forces caused by flow in
the bellows. The external seal and internal pressure
forces on the model were obtained by multiplying the
difference between the average pressure (external seal
or internal pressures) and free-stream static pressure
by the affected projected area normal to the modelaxis. The momentum tare force was determined from
calibrations using the Stratford choke nozzles prior to
the wind-tunnel investigation.
Axial force minus thrust was computed from
the main balance axial force from the following
F A - Fj = F A Mbal + (Pes,1 -- P_c)(Amb,1 - Aseal,1)
+ (Pi - Pcc)Aseal,1 - FA,mom - D/
(A1)
where the first term FA,Mbal includes all pressureand viscous forces (internal and external on both
the afterbody and thrust system). The second andthird terms account for the forward seal rim and
interior pressure forces, respectively. In terms of
an axial-force coefficient, the second term rangesfrom -0.0001 to -0.0007 and the third term varies
-t-0.0075 depending upon Mach number and pressure
ratio. The internal pressure at any given set of
test conditions was uniform throughout the inside
of the model, thus indicating no cavity flow. The
monmntum tare force FA,mo m is a momentum tarecorrection with jets operating and is a function of the
average bellows internal pressure, which is a function
of the internal chamber pressure in the supply pipes
just ahead of the sonic nozzles (fig. 5). Although
the bellows were designed to minimize momentum
and pressurization tares, small bellows tares still
exist with the jet on. These tares result from smallpressure differences between the ends of the bellows
when internal velocities are high and also from small
differences in the spring constants of the forward
and aft bellows when the bellows are pressurized.
The last term Df is the friction drag of the sectionfrom FS 44.75 to 48.25. A friction drag coefficient
of 0.0004 was applied at all Mach numbers. No
corrections were applied to the forces and moments
for the effects of angle of attack on this section.
The afterbody axial force is computed from a
similar relationship:
Raft = FA,Sbal + (Pes,2 -- Poc) (Arab,1 -- Aseal,1)
+ (Pi -Poc)Aseal,2 + (Pes,3 -Poc)
+ (Arab,2 - Aseal,2 ) (A2)
Since both balances are offset from the model cen-
terline, similar adjustments are made to the pitchingmoments measured by both balances. These adjust-
ments are necessary because both the pressure areaand bellows momentum tare forces are assumed to
act along the model centerline. The pitching-moment
tare is determined by multiplying the tare force by
the appropriate moment arm and subtracting the
value from the measured pitching moments.
11
Model Attitude
The adjusted forces and moments measured by
both balances are transferred from the body axis
of the metric portion of the model to the stability
axis. The attitude of the nonmetric forebody rel-ative to gravity was determined from a calibratedattitude indicator located in the model nose. The
angle of attack a, which is the angle between the
afterbody centerline and the relative wind, was de-
termined by applying terms for afterbody deflection(caused when the model and balance bend under
aerodynamic load) and a flow angularity term to theangle measured by the attitude indicator. The flow
angularity correction was 0.1 °, which is the aver-
age angle measured in the Langley 16-Foot TransonicTunnel.
Thrust-Removed Data
The resulting external and internal thrust forceand moment coefficients from the main balance in-
clude total lift coefficient CL,t, drag minus thrustcoefficient CD_F, total pitching-moment coefficient
Cm,t, total rolling-moment coefficient Cl,t, total-yawing-moment coefficient Cn,t, and total side-force
coefficient C_: t. Force and moment coefficients fromthe afterbody balance are afterbody lift coefficient
CL,af t, afterbody drag coefficient CD,aft, and after-
body pitching-moment coefficient Cm,aft.
The thrust-removed aerodynamic force and mo-ment coefficients for the entire model were obtained
by determining the components of thrust in axial
force, normal force, pitching moment, rolling mo-
ment, yawing moment, and side force, and thenby subtracting these values from the measured to-
tal (aerodynamic plus thrust) forces and moments.
These thrust components at forward speeds weredetermined from measured static data and were a
function of the free-stream static and dynamic pres-sures. The thrust-removed aerodynamic coefficientsare given as follows:
CL = CL,t -- Jet lift coefficient (A3)
CD -- CD_ F -.b Thrust coefficient (A4)
Cm = Cm,t - Jet pitching-moment coefficient (A5)
CI = Cl,t - Jet rolling-moment coefficient (A6)
Cn = Cn,t - Jet yawing-moment coefficient (AT)
Cy = Cy, t - Jet side-force coefficient (A8)
The nozzle coefficients are obtained by simply com-bining the measured results from both force balancesas follows:
CL,n = CL -- CL,aft (A9)
CD,n = CD -- CD,aft (A10)
Cm,n = Cm - Cm,aft (All)
Volume Coefficients
To facilitate the analysis of control-power char-acteristics, a powered volume coefficient is defined.
(See ref. 9.) The volume coefficient of the horizontaltail is
V- St LtS-_
where St is the horizontal tail area and Lt is thedistance from the moment reference center to the
quarter-chord of the tail. The pitch vectoringpowered-volume coefficient is defined as
where At is the nozzle throat area and Lj is thedistance from the moment reference center to the
nozzle throat. The throat area is multiplied by 2because the configuration reported on herein is atwin-engine model.
12
References
1. Herbst, W. B.: Future Fighter Technologies. J. Aircr.,
vol. 17, no. 8, Aug. 1980, pp. 561-566.
2. Gallaway, C. R.; and Osborn, R. F.: Aero-
dynamics Perspective of Supermaneuverability. AIAA-85-
4068, Oct. 1985.
3. Hienz, Egon; and Vedova, Ralph: Requirements, Defini-
tion and Preliminary Design for an Axisymmetric Vector-
ing Nozzle, To Enhance Aircraft Maneuverability. AIAA-
84-1212, June 1984.
4. Skow, Andrew M.; Hamilton, William L.; and Taylor,
John H.: Advanced Fighter Agility Metrics. AIAA-85-
1779, Aug. 1985.
5. Miller, L. Earl: Post Stall Maneuvers and Thrust Vec-
toring Performance Analysis. AFWAL-TR-84-3109, U.S.
Air Force, July 1984. (Available from DTIC as AD A158
100.)
6. Richey, G. K.; Surber, L. E.; and Berrier, B. L.: Airframe-
Propulsion Integration for Fighter Aircraft. AIAA-83-
0084, Jan. 1983.
7. Nelson, B. D.; and Nicolai, L. M.: Application of Multi-
Function Nozzles to Advanced Fighters. AIAA°81-2618,
Dec. 1981.
8. Mello, J. F.; and Kotansky, D. R.: Aero/Propulsion
Technology for STOL and Maneuver. AIAA-85-4013,
Oct. 1985.
9. Capone, Francis J.; and Mason, Mary L.: Multiaxis
Aircraft Control Power From Thrust Vectoring at High
Angles of Attack. NASA TM-87741, 1986.
10. Capone, Francis J.; and Bare, E. Ann: Multiaxis Control
Power From Thrust Vectoring for a Supersonic Fighter
Aircraft Model at Mach 0.20 to 2.47. NASA TP-2712,
1987.
11. Capone, Francis J.: Static Performance of Five Twin-
Engine Nonaxisymmetric Nozzles With Vectoring and Re-
versing Capability. NASA TP-1224, 1978.
12. Capone, Francis J.; and Reubush, David E.: Effects of
Varying Podded Nacelle-Nozzle Installations on Transonic
Aeropropulsive Characteristics of a Supersonic Fighter
Aircraft. NASA TP-2120, 1983.
13. Capone, Francis J.; and Berrier, Bobby L.: Investigation
of Axisymmetric and Nonaxisymmetric Nozzles Installed
on a 0.10-Scale F-18 Prototype Airplane Model. NASA
TP-1638, 1980.
14. Mason, Mary L.; and Berrier, Bobby L.: Static In-
vestigation of Several Yaw Vectoring Concepts on Non-
axisymmetric Nozzles. NASA TP-2432, 1985.
15. Mason, Mary L.; and Berrier, Bobby L.: Static Perfor-
mance of Nonaxisymmetric Nozzles With Yaw Thrust-
Vectoring Vanes. NASA TP-2813, 1988.
16. Taylor, John G.: A Static Investigation of a Simultaneous
Pitch and Yaw Vectoring 2-D C-D Nozzle. AIAA-88-2998,
July 1988.
17. Peddrew, Kathryn H., compiler: A User's Guide to the
Langley 16-Foot Transonic Tunnel. NASA TM-83186,
1981.
18. Mercer, Charles E.; Berrier, Bobby L.; Capone, Francis J.;
Grayston, Alan M.; and Sherman, C. D.: Computations
for the 16-Foot Transonic Tunnel--NASA, Langley Re-
search Center, Revision 1. NASA TM-86319, 1987. (Su-
persedes NASA TM-86319, 1984.)
19. Stevens, H. L.; Thayer, E. B.; and Fullerton, J. F.: De-
velopment of the Multi-Function 2-D/C-D Nozzle. AIAA-
81-1491, July 1981.
20. Yetter, Jeffery A.; and Leavitt, Laurence D.: Effects
of Sidewall Geometry on the Installed Performance of
Nonaxisymmetric Convergent-Divergent Exhaust Nozzles.
NASA TP-1771, 1980.
21. Capone, Francis J.; and Mason, Mary L.: Interference Ef-
fects of Thrust Reversing on Horizontal Tail Effectiveness
of a Twin-Engine Fighter Aircraft at Mach Numbers From
0.15 to 0.90. NASA TP-2350, 1984.
22. Re, Richard J.; and Leavitt, Laurence D.: Static Internal
Performance Including Thrust Vectoring and Reversing of
Two-Dimensional Convergent-Divergent Nozzles. NASA
TP-2253, 1984.
23. Capone, Francis J.; and Carson, George T., Jr.: Effects
of Empennage Surface Location on Aerodynamic Charac-
teristics of a Twin-Engine Afterbody Model With Non-
axisymmetric Nozzles. NASA TP-2392, 1985.
13
Table 1. Index to Data in Tables 2 to 13
Table
2, 34
5
6
7
8
9
10, 11
12, 13
Power
settingAfterburner
!
Dry
Sidewall,
left/right
100/100 A/B
50/50 A/B
25/25 A/B
100/100 dry
100/100 A/B
50/50 A/B
25/25 A/B
100/25 A/B
100/25 A/B
_v,p, deg0
15
15
15
0
0
14
Table2. LongitudinalAerodynamicCharacteristicsfor A/B NozzleWith 100/100A/B Sidewallsand_v,p= 0°
(a) Total aft end
MACH NPR ALPHA CLT C(D-F) CMT CL CD CM
.99
3.01
4.96
6.99
8.97
.99
.98
93
90
88
80
70
67
7.03
7.00
6.96
7.02
7.05
6.99
7.00
6.99
1.I0
1.98
3.01
4.99
7.00
i. I0
i.i0
1.09
i. I0
I.i0
i. I0
1.09
1.07
5.01
5.00
5.01
4.99
5.00
5.01
4.99
5.O0
.00 -.0098
.02 -.0100
.04 -.0109
.04 -.0114
.03 -.0111
-2.02 -.0224
.01 -.0091
3.01 .0063
5.98 .0223
9.03 .0358
12.02 .0486
16.01 .0655
18.01 .0747
-2.01 -.0218
-.02 -.0093
3.02 .0083
6.01 .0287
8.98 .0479
11.99 .0660
16.02 .0896
17.98 .1008
-.01 -.0107
-.02 -.0088
.00 -.0097
.02 -.0097
.00 -.0101
-2.01 -.0086
-.02 -.0090
2.99 -.0044
6.01 -.0062
8.99 -.0021
12.01 .0141
16.01 .0299
18.02 .0382
-1.99 -.0125
.00 -.0098
3.03 .0003
5.99 .0037
9.00 .0141
12.01 .0356
16.02 .0605
18.01 .0734
1.201
1.202
1.202
1.203
1.202
1.199
1.202
1.201
1.198
1.200
1.198
1.200
1.202
1.199
1.201
1.201
1.203
1.201
1.199
1.200
I 199
903
9OO
901
898
9OO
899
902
.899
.901
.901
.902
.899
.899
9OO
901
901
899
901
903
900
901
.0166 0031
-.0151 0069
-.0450 0117
-.0773 0156
-.1087 0183
.0178 0137
.0165 0026
.0178 -.0083
.0212 -.0201
.0271 -.0294
.0371 -.0455
.0479 -.0634
.0542 -.0738
-.0764 .0203
-.0769 .0147
-.0755 .0083
-.0732 -.0024
-.0679 -.0144
-.0590 -.0289
-.0476 -.0473
-.0417 -.0558
.0033 0059
-.0245 0066
-.0511 0110
-.1054 0168
-.1605 0224
.0033 0038
.0034 0054
.0029 0056
.0022 0075
.0029 0064
.0074 -.0033
.0173 -.0152
.0248 -.0225
-.1052 .0152
-.1055 .0169
-.1060 .0167
-.1064 .0190
-.1050 .0175
-.0992 .0075
-.0874 -.0066
-.0785 -.0151
-.0098
-.0100
-.0109
-.0115
-.0112
-.0224
-.0091
0063
0223
0359
0487
0656
0748
-.0186
-.0093
0036
0192
0337
0471
0645
0726
-.0107
-.0088
-.0097
-.0097
-.0101
-.0086
-.0090
-.0044
-.0062
-.0020
.0142
.0300
.0384
-.0088
-.0098
-.0054
-.0076
-.0028
.0131
.0307
.0401
0166
0158
0153
0136
0121
0178
0165
0178
0212
0271
0371
0479
0542
0155
.0144
.0149
.0175
.0229
.0304
.0402
.0453
.0033
.0034
.0040
.0033
.0020
.0033
.0034
.0029
.0022
.0029
.0074
.0173
.0248
.0033
.0029
.0023
.0016
.0022
.0066
.0168
.0245
0031
0041
0060
0069
0066
0137
0026
-.0083
-.0201
-.0294
-.0455
-.0634
-.0738
.0114
.0060
-.0005
-.Oll2
-.0233
-.0376
-.0561
-.0646
.0059
.0042
.0059
.0065
.0068
.0038
.0054
.0056
.0075
.0064
-.0033
-.0152
-.0225
.0049
.0066
.0063
.0087
.0072
-.0O28
-.0170
-.0254
15
Table 2. Continued
(a) Continued
MACH
.601
.599
.601
602
603
604
600
602
603
601
600
600
598
599
6OO
•602
.599
.598
599
600
601
597
602
602
.602
•601
.600
.599
.599
•600
.600
.598
.599
.599
.598
.596
.600
.600
NPR
1.03
1.99
3.00
3.52
5.01
1.03
1.03
1.03
1.03
1.03
1.03
1.02
1.02
3.51
3.52
3.51
3.50
3.49
3.49
3.49
3.50
1.02
2.02
3.05
3.51
5.01
1.02
1.02
1.02
1.00
.99
.96
3.53
3.46
3.49
3.48
3.50
3.5O
ALPHA
.01
.02
-.02
-.02
-.02
-1.94
.00
3.01
6.00
9.00
12.02
16.00
18.03
-1.85
.01
3.00
5.97
8.99
12.00
15.99
18.00
20.01
20.01
20.01
20.00
20.02
16.63
17.99
19.98
23.97
27.98
31.99
16.79
17.99
19.98
23.96
27.97
31.98
CLT
-.0111
-.0090
-.0096
-.0092
-.0087
-.0065
-.0045
-.0023
.0013
.0052
.0099
.0255
.0340
-.0118
-.0050
0062
0172
0296
0429
0692
0827
0413
0633
0843
.0938
.1251
.0267
.0321
.0396
.0572
.0769
.0921
.0710
.0785
.0925
.1216
.1542
.1822
C(D-F)
.0037
-.0609
-.1194
-.1501
-.2386
.0052
.0043
.0040
.0042
.0052
.0068
.0127
.0176
-.1504
-.1509
-.1490
-.1490
-.1471
-.1437
-.1346
-.1279
.0234
-.0393
-.0958
-.1220
-.2085
.0144
.0173
.0225
.0375
.0584
.0831
-.1360
-.1281
-.1231
-.1047
-.0771
-.0455
CMT
0O55
0101
0171
0199
0283
0033
0031
0032
.0016
-.0013
-.0059
-.0182
-.0241
.0195
.0187
.0176
.0165
.0131
.0079
-.0055
-.0119
-.0293
-.0236
-.0189
-.0166
-.0086
-.0196
-.0232
-.0292
-.0463
-.0714
-.I010
-.0057
-.0098
-.0160
-.0354
-.0661
-.1007
CL
-.0111
-.0090
-.0096
-.0092
-.0087
-.0065
-.0045
-.0023
.0013
.0052
.0100
.0256
.0341
-.0068
-.0050
-.0018
.0012
.0056
.0110
.0272
.0356
.0415
.0412
.0415
.0416
.0415
.0268
.0322
.0398
.0573
.0771
.0923
.0262
.0318
.0402
.0591
.0825
.1013
CD
.0037
•0032
.0043
.0034
•0038
.0052
.0043
.0040
.0042
.0052
.0068
.0127
.0176
.0040
.0037
.0037
.0039
.0049
.0067
.0125
.0174
.0234
.0218
.0223
.0220
.0213
.0144
.0173
.0226
.0375
0585
0832
0129
0162
0213
0364
0583
0844
CM
.0055
.0046
.0056
.0054
.0052
.0033
.0031
.0032
.0016
-.0013
-.0059
-.0182
-.0241
.0050
.0042
.0032
.0021
-.0013
-.0066
-.0198
-.0262
-.0293
-.0292
-.0306
-.0310
-.0320
-.0196
-.0232
-.0292
-.0463
-.0714
-.I010
-.0203
-.0240
-.0304
-.0499
-.0805
-.1151
16
Table 2. Continued
(a) Concluded
MACH
152
153
153
153
154
151
151
152
152
152
152
151
.151
153
153
154
154
154
151
151
150
152
151
152
152
145
149
151
151
151
151
151
151
150
152
152
152
152
152
152
151
NPR
1.00
2.02
2.60
3.00
3.81
1.00
1.00
1.00
1.00
1.00
1.00
1.00
1.00
2.63
2 65
2 62
2 62
2 63
2 62
2 62
2.62
1.00
2.03
2.58
3.01
3.83
3.83
1.00
1.00
1.00
1.00
1.00
1.00
i.O0
2.58
2.64
2.63
2.63
2.63
2.63
2.63
ALPHA
.00
-.01
.00
.00
.00
-1.53
-.01
2.98
6.02
8.98
11.99
16.02
17.99
-1.54
.04
3.02
6.00
9.00
12.00
16.01
18.00
19.99
19.98
19.98
19.99
19.98
19.99
15.98
17.98
19.98
23.98
27.98
31.99
35.18
15.97
17.97
19.97
23.97
27.97
31.97
34.98
CLT
.0073
.0193
.0102
.0056
.0041
.0062
.0097
.0121
.0157
.0247
.0276
.0403
.0469
-.0412
-.0012
.0846
.1648
.2496
.3478
.4743
.5389
.0330
.3900
.5604
.6946
1.0548
.9980
.0310
.0507
.0573
.0685
.0937
.1085
.1125
.4668
.5467
.5949
.7119
.8189
.9369
1.0213
C(D-F)
.0085
-1.0161
-1.5133
-1.8833
-2.6051
-.0033
.0017
-.0016
-.0034
-.0005
.0049
.0076
.0104
-1.5609
-1.5664
-1.5270
-1.5273
-1.5146
-1.5540
-1.5296
-1.5157
.0228
-.9462
-1.4225
-1.7909
-2.7861
-2.6255
.0116
.0171
.0249
.0354
.0586
.0800
.0977
-1.4334
-1.4758
-1.4438
-1.4010
-1.3410
-1.2771
-1.2245
CMT
-.0060
.0737
.1304
.1798
.2522
-.0012
-.0018
-.0018
-.0009
-.0065
-.0104
-.0207
-.0261
1499
1529
1432
1447
1416
1422
1286
1235
-.0294
.0594
.1153
.1581
.2645
.2477
-.0179
-.0305
-.0360
-.0446
-.0655
-.0874
-.1028
.1159
.1162
.1143
.1055
.0903
.0695
.0503
CL
.0073
.0194
.0102
.0055
.0040
.0062
.0097
.0121
.0157
.0247
.0276
.0404
.0471
.0011
-.0024
.0035
.0034
.0083
.0159
.0313
.0409
.0331
.0377
.0327
.0334
.0357
.0363
.0311
.0508
.0574
.0687
.0939
.1087
.1127
.0458
.0547
.0551
.0670
.0742
.0915
.0984
CD
.0085
-. 0036
.0141
.0122
.0018
-.0033
.0017
-.0016
-.0034
-.0005
.0049
.0076
.0104
.0087
.0101
.0100
.0084
.0090
.0076
.0147
.0175
.0228
.0236
.0289
.0274
.0168
.0191
.0116
.0172
.0250
.0354
.0587
.0801
.0978
.0385
.0413
.0420
.0496
.0617
.0777
.0948
CM
-.0060
-.0135
-.0083
.0044
.0059
-.0012
-.0018
-.0018
-.0009
-.0065
-.0104
-.0207
-.0261
.0071
.0094
.0033
.0043
.0013
-.0030
-.0175
-.0231
-.0294
-.0295
-.0247
-.0210
-.0174
-.0184
-.0179
-.0305
-.0360
-.0446
-.0655
-.0874
-.1028
-.0229
-.0290
-.0295
-.0389
-.0542
-.0758
-.0962
17
Table 2. Continued
(b) Afterbody and nozzle
MACH NPR ALPHA CLAFT CDAFT CMAFT CLN CDN CMN
1.201
1.202
1.202
1.203
1.202
1 199
1 202
1 201
1 198
1 200
1 198
1 200
1 202
1 199
1 201
1 201
1.203
1.201
1.199
1.200
1.199
.903
.900
.901
.898
.900
.899
.902
.899
.901
.901
.902
.899
.899
.900
.901
.901
.899
.901
.903
.900
.901
.99
3.01
4.96
6.99
8.97
.99
.98
.93
.90
.88
.80
.70
.67
7.03
7.00
6.96
7.02
7.05
6.99
7.00
6.99
1.10
1.98
3.01
4.99
7. O0
I.I0
I.I0
1.09
I.I0
1.10
1.10
1.09
1.07
5.01
5. O05.01
4.99
5.005.01
4.99
5.00
.00
.02
.04
.04
.03
-2.02
.01
3.01
5.98
9.03
12.02
16.O1
18.01
-2.01
-.02
3.02
6.01
8.98
11.99
16.02
17.98
-.01
-.02
.00
.02
.00
-2.01
-.02
2 99
60l
8 99
12 Ol
16 Ol
18 02
-1.99
.00
3.03
5.99
9.00
12.01
16.02
18.01
-.0081
-.0079
-.0078
-.0080
-.0078
-.0163
-.0078
.0036
.0174
.0301
.0405
.0534
.0594
-.0164
-.0084
.0036
.0182
.0300
0408
0536
0589
- 0033
- 0032
- 0033
- 0034
-.0034
-.0018
-.0032
-.0049
-.0060
-.0047
-.0005
.0138
.0189
-.0017
-.0032
-.0050
-.0055
-.0043
.0003
.0151
.0203
.0084
.0084
.0084
.0085
.0085
.0091
.0086
.0092
.0114
.0150
.0199
.0266
.0305
.0093
.0087
.0093
0116
0152
0199
0269
0305
0060
0055
0055
0054
0052
0059
0060
0059
0056
0058
0073
.0142
0188
0053
0054
0053
0050
0052
0070
0141
0187
.0077
.0075
.0075
.0075
.0074
.0145
.0073
-.0022
-.0153
-.0284
-.0418
-.0562
-.0632
.0144
.0078
-.0025
-.0163
- 0289
- 0421
- 0569
- 0626
0028
0027
0028
.0029
.0028
0010
0026
0051
0066
0070
0051
-.0055
-.0093
0009
0027
0054
0063
0067
0044
-.0071
-.0112
-.0017
-.0021
-.0031
-.0035
-.0034
-.0060
-.0013
.0027
.0050
.0058
.0082
.0122
.0154
-.0022
-.0009
.0000
.0011
.0037
0063
0110
0138
- 0075
- 0O56
- 0064
- 0063
- 0067
-.0069
-.0059
.0005
-.0002
.0027
.0147
.0162
.0195
-.0071
-.0066
-.0004
-.0021
.0015
.0129
.0156
.0198
.0082
.0074
.0069
.0051
.0036
.0086
.0080
.0086
.0098
.0121
.0172
.0213
.0237
.0063
.0057
.0056
.0059
0077
0105
0133
0149
- 0027
- OO20
- 0016
- 0021
-.0032
-.0026
-.0027
-.0030
-.0034
-.0029
.O000
.0031
.O061
-.0020
-.0024
-.0030
-.0034
-.0031
-.0003
.0027
.0058
-.0046
-.0034
-.0015
-.0007
-.0008
-.0008
-.0047
-.0061
-.0048
-.0010
-.0037
-.O071
-.O106
-.0030
-.0018
.0020
.0051
.0057
0044
0007
- 0020
0031
0015
0030
0035
.0040
.0028
.0028
.0005
.0009
-.0005
-.0084
-.0097
-.0132
.0039
.0039
.0009
.0023
.0005
-.0072
-.0099
-.0142
18
Table 2. Continued
(b) Continued
MACH
.601
.599
.601
.602
.603
.604
.600
.602
.603
•601
.600
.600
.598
.599
.600
.602
.599
598
599
600
601
597
602
602
602
601
600
599
599
6O0
.600
.598
.599
.599
.598
.596
.600
•600
NPR ALPHA CLAFT CDAFT CMAFT
1.03
1.99
3.00
3.52
5.01
1.03
1.03
1.03
1.03
1.03
1.03
1.02
1.02
3.51
3.52
3.51
3.50
3.49
3.49
3.49
3.50
1.02
2.02
3 05
3 51
5 01
1 02
1 02
1 02
1 00
.99
.96
3.53
3.46
3.49
3.48
3.50
3.50
.01
.02
-.02
-.02
-.02
-1.94
.00
3.01
6.00
9•00
12.02
16.00
18.03
-1.85
.01
3.00
5.97
8.99
12.00
15.99
18.00
20.01
20.01
20.01
20.00
20.02
16.63
17.99
19.98
23.97
27.98
31.99
16.79
17.99
19.98
23.96
27.97
31.98
-.0032
-.0031
-.0031
-.0029
-.0031
-.0041
-.0028
-.0019
-.0004
.0019
.0050
.0148
.0197
-.0035
-.0025
-.0016
-.0002
.0021
.0055
.0154
.0206
.0224
.0230
.0231
.0233
.0234
0149
0177
0223
0363
0510
0665
0156
0181
.0228
.0372
.0530
.0699
.0055 .0029
.0052 .0026
.0052 .0027
.0052 .0025
.0051 .0027
.0056 .0032
.0054 .0024
.0054 .0024
.0056 .0014
.0061 -.0007
.0072 -.0042
.0108 -.0137
.0133 -.0177
.0052 .0026
.0051 .0022
.0051 .0022
.0053 .0014
.0058 -.0008
.0069 -.0046
0105 -.0142
0133 -.0186
0156 -.0215
0156 -.0221
0156 -.0224
0157 -.0226
0157 -.0229
0109 -.0148
0125 -.0171
0156 -.0215
0255 -.0370
0389 -.0573
0566 -.0835
0109 -.0156
0123 -.0176
0155 -.0221
.0256 -.0382
.0398 -•0603
.0586 -.0886
CLN
-.0079
-.0059
-.0065
-.0062
-.0056
-.0025
-.0017
-.0004
.0017
.0033
.0050
.0108
.0144
-.0033
-.0025
-.0002
.0015
.0035
.0055
.0118
.0150
.0190
.0182
.0183
0183
0181
0119
0145
0174
0210
0261
0258
0106
.0137
.0174
.0219
.0295
.0314
CDN
-.0018
-.0020
-.0009
-.0018
-.0013
-.0004
-.0011
-.0015
-.0014
-.0009
-.0003
.0019
.0043
-.0011
-.0013
-.0014
-.0014
-.0009
-.0002
.0020
.0041
.0079
.0062
.0067
.0063
0056
0034
0048
0070
0121
0196
.0266
.0020
.0038
.0059
.0107
.0185
.0258
CMN
.0026
.0020
.0029
.0029
.0025
.0002
.0007
.0007
.0002
-.0006
-.0017
-.0045
-.0064
.0024
.0020
.0010
.0007
-.0005
-.0019
-.0057
-.0076
-.0078
-.0070
-.0082
-.0084
-.0091
-.0048
-.0062
-.0077
-•0093
-.0141
-.0175
-.0046
-.0064
-.0083
-.0117
-.0202
-.0264
19
Table 2. Concluded
(b) Concluded
MACH NPR ALPHA CLAFT CDAFT CMAFT CLN CDN CMN
152 1.00 .00
153 2.02 -.01
153 2.60 .00
153 3.00 .00
154 3.81 .00
151 1.00 -1.53
151 1.00 -.01
152 1.00 2.98
152 1.00 6.02
152 1.00 8.98
152 1.00 11.99
151 1.00 16.02
151 1.00 17.99
153 2.63 -1.54
153 2.65 .04
154 2.62 3.02
154 2.62 6.00
154 2.63 9.00
151 2.62 12.00
151 2.62 16.01
150 2.62 18.00
152 1.00 19.99
151 2.03 19.98
152 2.58 19.98
152 3.01 19.99
145 3.83 19.98
149 3.83 19.99
151 1.00 15.98
151 1.00 17.98
151 1.00 19.98
151 1.00 23.98
151 1.00 27.98
151 1.00 31.99
150 1.00 35.18
152 2.58 15.97
152 2.64 17.97
152 2.63 19.97
152 2.63 23.97
.152 2.63 27.97
.152 2.63 31.97
.151 2.63 34.98
-.0016
-.0032
-.0032
-.0031
-.0043
-.0020
-.0016
-.0017
-.0002
.0024
.0070
.0135
.0183
-.0021
-.0025
.0011
.0008
.0010
.0048
.0132
.0191
.0175
.0181
0181
0181
0167
0184
0103
0165
0206
0272
0392
0522
0575
0102
.0175
.0209
.0271
.0390
.0522
.0620
.0064
.0071
.0071
.0076
.0077
.0058
.0057
.0058
.0059
.0066
.0081
.0107
.0132
.0069
.0067
.0070
.0070
.0074
.0087
.0120
0147
0137
0141
0140
0142
0142
0147
0086
.0108
0130
0185
0288
0428
0521
0095
0122
0144
0195
0299
0440
0566
.0006
.0026
.0034
.0035
.0047
.0014
.OO11
.0028
.0017
-.0008
-.0062
-.0127
-.0174
.0024
.0033
-.0004
.0001
.0007
-.0043
-.0134
- 0197
- 0199
- 0211
- 0207
- 0208
- 0191
- 0210
- 0104
- 0172
-.0214
-.0270
-.0419
-.0611
-.0715
-.0094
-.0188
-.0218
-.0283
-.0426
-.0617
-.0783
.0088
.0226
.0134
.0086
.0083
.0082
.0113
.0138
.0159
.0224
.0206
.0269
.0288
.0032
.0001
.0024
.0026
.0073
0110
0180
0219
0156
0195
0146
0153
0190
0179
O208
0343
.0368
.0415
.0546
.0565
.0552
.0357
.0372
.0342
.0399
.0352
.0394
.0364
.0022
-.0106
.0070
.0047
-.0059
-.0091
-.0040
-.0075
-.0093
-.0071
-.0032
-.0030
-.0028
.0018
.0034
.0030
.0014
.0015
-.0011
.0026
.0028
.0091
.0095
.0150
.0132
.0026
0044
0030
0064
0120
0169
0299
0373
0457
0289
0290
0277
.0301
.0319
.0337
.0382
-.0065
-.0161
-.0117
.0010
.0012
-.0026
-.0030
-.0047
-.0026
-.0056
-.0041
-.0079
-.0087
.0047
.0061
.0037
.0042
.0006
.0014
-.0041
- 0034
- 0094
- 0084
- 0040
- O001
O017
0026
- 0075
-.0133
-.0146
-.0177
-.0236
-.0262
-.0312
-.0135
-.0101
-.0077
-.0106
-.0116
-.0141
-.0179
2O
Table 3. Lateral Aerodynamic Characteristics for A/B Nozzle With 100/100 A/BSidewalls and 5v,p = 0°
MACH NPR ALPHA CROLLT CNT CYT CROLL CN CY
1.201
1.2021.202
1.203
1 202
1 199
1 202
1 201
1 198
1 200
1.198
1.200
1.202
1.199
1.201
1.201
1.203
1.201
1.199
1.2001.199
9039OO
901
898
9OO
899
902
899
901901
902
899
899
90O901
901
.899
.901
.903
.900
.901
9930l
4 96
6 99
8 97
99
98
93
9O
88
80
70
67
7 03
7.O0
6.96
7.02
7.05
6.99
7.006.99
i.I0
1.98
3.01
4.99
7.00
I.lO
I.I0
1.09
i.I0i.i0
1.10
1.09
1.07
5.01
5.O0
5.01
4.99
5.00
5.01
4.995.O0
00
0204
04
03
-2 02
01
3 O1
5.98
9.03
12.02
16.01
18.01
-2.01
-.02
3.02
6.01
8.98
11.99
16.0217.98
-.01
-.02
.00
.02
.00
-2.01
-.02
2.99
6.018.99
12.01
16.01
18.02
-1.99
.00
3.03
5.99
9.00
12.01
16.0218.01
0000
00000001
0001
0001
0001
0001
0001
0001
0002
0001
0001
0002
0002
0002
0002
0002
00030002
0002
0002
.0003
.0003
.0003
.0003
.0003
.0002
.0003
.0002
.0002
.0002
.0002
.0002
0002
0002
0002
0002
0002
0002
.0002
.0002
.0002
0002
00030003
0003
0003
0001
0003
0004
0004
0005
0003
0003
0003
0004
0005
0006
0007
0011
00040001
0000
.0005
.0006
.0005
.0005
.0005
.0004
.0005
.0005
.0005
.0004
.0003
.0002
.0003
.0004
0005
0005
0005
0005
00030002
0003
-.0007-.0011
-.0012
-.0014
-.0015
-.0007
-.0008
-.0013
-.0015
-.0019
-.0018
- 0015
- 0013
- 0022
- 0025
- 0028
- 0030
- 0034- 0031
- 0022
- 0018
- 0024
- 0028
- 0029
- 0032
- 0036
- 0023
-.0025-.0025
-.0023
-.0022
-.0021
-.0018
-.0021
-.0029
-.0030
-.0029
-.0029
-.0029-.0025
-.0024
-.0026
•0000 .0002 -.0007
•0000 .0003 -.0011•0001 .0003 -.0012
•0001 .0003 -.0014
•0001 .0003 -.0015
.0001 .0001 -.0007
.0001 .0003 -.0008
.0001 .0004 -.0013
.0001 .0004 -.0015
.0002 .0005 -.0019
.0001 .0003 -.0018
.0001 .0003 -.0015
.0002 .0003 -.0013
.0002 .0004 -.0022
.0002 .0005 -.0025
.0002 .0006 -.0028
.0002 .0007 -.0030
.0003 .0011 -.0034
.0002 .0004 -.0031
.0002 .0001 -.0022
.0002 .0000 -.0018
.0003 .0005 -.0024
•0003 .0006 -.0028
.0003 .0005 -.0029
.0003 .0005 -.0032
.0003 .0005 -.0036
.0002 .0004 -.0023
.0003 .0005 -.0025
.0002 .0005 -.0025
.0002 .0005 -.0023
.0002 .0004 -.0022
.0002 .0003 -.0021
.0002 .0002 -.0018
.0002 .0003 -.0021
.0002 .0004 -.0029
.0002 .0005 -.0030
.0002 .0005 -.0029
.0002 .0005 -.0029
.0002 .0005 -.0029
.0002 .0003 -.0025
.0002 .0002 -.0024
.0002 .0003 -.0026
21
Table 3. Continued
MACH
•601
599
601
602
603
604
600
602
603
601
600
600
598
599
600
602
599
598
599
600
601
597
602
602
602
601
6O0
599
599
600
600
598
599
599
598
596
600
600
NPR
1.03
1.99
3.00
3 52
50l
1 03
1 03
1 03
1 03
1 03
1 03
1 O2
1 02
3 51
3 52
3 51
3 50
3 49
3 49
3 49
3 50
1 02
2.02
3.05
3.51
5.01
1.02
1.02
1 02
1 00
99
96
3 53
3 46
3 49
3.48
3.50
3.50
ALPHA
01
02
- 02
- 02
- 02
-I 94
00
3 01
6.00
9.00
12.02
16.00
18.03
-1.85
.01
3.00
5.97
8.99
12.00
15.99
18.00
20.01
20.01
20.01
20.00
20.02
16.63
17.99
19.98
23.97
27.98
31.99
16.79
17.99
19.98
23.96
27.97
31.98
CROLLT CNT CYT
OOO2
0002
0002
OO02
0002
0003
0004
0004
0004
0003
0003
0003
0003
0002
0002
0002
0002
0002
0003
0002
0003
0001
0002
0002
0002
0002
.0000
.0000
.0001
.0011
.0018
.0016
.0001
.0001
.0002
.0012
.0019
.0018
0002 -.0015
0006 -.0024
0003 -.0026
0004 -.0028
0004 -.0033
0005 -.0029
0004 -.0028
0005 -.0028
0005 -.0028
0005 -.0028
0006 -.0028
0005 -.0026
0006 -.0028
0004 -.0032
0004 -.0029
0004 -.0032
0004 -.0032
0004 -.0032
0006 -.0035
.0005 -.0032
.0007 -.0040
.0006 -.0020
.0011 -.0035
.0011 -.0039
.0010 -.0041
.0012 -.0050
.0002 -.0011
.0002 -.0012
•0007 -.0025
.0078 -.0188
.0128 -.0275
.0127 -.0266
.0004 -.0021
.0005 -.0025
.0012 -.0045
.0082 -.0206
.0133 -.0298
.0141 -.0304
CROLL
0002
0002
0002
0002
0002
0003
0004
0004
0004
0003
0003
0003
0003
0002
0002
0002
0002
0002
0003
0002
0003
0001
0002
0002
0002
.0002
.0000
.0000
.0001
.0011
.0018
.0016
.0001
.0001
.0002
.0012
.0019
.0018
CN
0002
0OO6
0003
0004
0004
0005
0004
0005
0005
00O5
0006
0005
0006
0004
0004
0004
OOO4
.OOO4
.0006
.0005
.0007
.0006
.O011
.OOll
.0010
.0012
.0002
.0002
.0007
.0078
.0128
.0127
.0004
.0005
.0012
.0082
.0133
.0141
CY
-.0015
-.0024
-.0026
-.0028
-.0033
-.0029
-.0028
-.0028-.0028
-.0028
-.0028
-.0026
-.0028
-.0032
-.0029
-.0032
-.0032
-.0032
-.0035
-.0032
-.0040
-.0020
-.0035
-.0039
-.0041
-.0050
-.0011
-.0012
-.0025
-.0188
-.0275
-.0266
-.0021
-.0025
-.0045
-.0206
-.0298
-.0304
22
Table 3. Concluded
MACH
152
153
153
153
154
151
151
152
152
152
152
151
151
153
.153
.154
154
154
151
151
150
152
151
152
152
145
149
151
151
151
151
151
151
.150
152
152
152
152
152
152
151
NPR
1.00
2.02
2.60
3.00
3.81
1.00
i. 00
I. 00
I. 00
I. 00
i. 00
1.00
1.00
2.63
2.65
2.62
2.62
2.63
2.62
2.62
2.62
1.00
2.03
2.58
3.01
3.83
3.83
I.00
i. 00
I. 00
I. 00
1.00
1.00
1.00
2.58
2.64
2.63
2.63
2.63
2.63
2.63
ALPHA
.00
-.01
.00
.00
.00
-1.53
-.01
2.98
6.02
8.98
11.99
16.02
17.99
-1.54
.04
3.02
6.00
9.00
12.00
16.01
18.00
19.99
19.98
19.98
19.99
19.98
19.99
15.98
17.98
19.98
23.98
27.98
31.99
35.18
15.97
17.97
19.97
23.97
27.97
31.97
34.98
CROLLT CNT CYT
.0029
.0032
.0028
.0020
.0016
.0020
.0018
.0018
.0018
.0015
.0014
.0011
.0011
.0005
.0007
.0010
.0006
.0009
.0007
.0004
.0003
.0020
.0016
.0009
.0007
.0006
0005
0015
0014
0014
0010
0012
0006
0009
0013
0010
0009
0006
0006
-.0005
-.0006
.0037
.0093
.0062
.0043
.0030
.0029
.0033
.0033
.0037
.0043
.0037
.0043
.0049
.0029
.0028
.0041
.0039
.0047
.0047
.0043
.0051
.0010
.0085
.0071
.0050
.0056
.0052
.0017
.0016
.0017
.0011
.0020
-.0023
-.0023
.0066
0064
0062
0051
0072
0016
0010
-.0222
-.0376
-.0352
-.0352
-.0365
-.0174
-.0188
-.0170
-.0170
-.0170
-.0135
-.0134
-.0152
-.0228
-.0197
-.0245
-.0212
-.0243
-.0218
-.0197
-.0201
-.0041
-.0251
-.0253
-.0237
-.0305
-.0287
-.0075
-.0059
-.0058
-.0037
-.0042
.0061
.0048
-.0252
-.0250
-.0232
-.0209
-.0233
-.0078
-.0073
CROLL
.0029
.0032
.0028
.0020
.0016
.0020
.0018
.0018
.0018
.0015
.0014
.0011
.0011
.0005
.0007
.0010
.0006
.0009
.0007
.0004
.0003
0020
0016
0009
0007
0006
0005
0015
0014
0014
0010
0012
0006
0009
0013
0010
.0009
.0006
.0006
-.0005
-.0006
CN
.0037
.0093
.0062
.0043
.0030
.0029
.0033
.0033
.0037
.0043
.0037
.0043
.0049
.0029
.0028
.0041
.0039
.0047
.0047
.0043
.0051
.0010
0085
0071
0050
0056
0052
0017
0016
0017
0011
0020
- 0023
- 0023
0066
0064
.0062
.0051
.0072
.0016
.0010
CY
-.0222
-.0376
-.0352
-.0352
-.0365
-.0174
-.0188
-.0170
-.0170
-.0170
-.0135
-.0134
-.0152
-.0228
-.0197
-.0245
-.0212
-.0243
-.0218
-.0197
-.0201
-.0041
-.0251
- 0253
- 0237
- 0305
- 0287
- 0075
- 0059
- 0058
- 0037
- 0042
.0061
.0048
-.0252
-.0250
-.0232
-.0209
-.0233
-.0078
-.0073
23
Table 4. Longitudinal Aerodynamic Characteristics for A/B Nozzle With 50/50 A/BSidewalls and 5v,p = 0 °
(a) Total aft end
MACH NPR ALPHA CLT C(D-F) CMT CL CD CM
1.201
1.201
1.200
1.201
1.201
.902
.901
900
897
900
598
598
600
600
602
.97 .01 -.0096 .0173
3.01 .02 -.0086 -.0150
5.00 .02 -.0104 -.0452
7.06 .02 -.0108 -.0774
9.03 .02 -.0111 -.1084
i. I0 .00 -.0108 .0033
2.02 .02 -.0108 -.0264
3.00 .02 -.0111 -.0518
4.99 .O1 -.0109 -.1058
7.01 .02 -.0108 -.1599
1.03 .01 -.0085 .0039
2.02 .02 -.0069 -.0626
3.01 .01 -.0068 -.1197
3.58 .02 -.0067 -.1542
5.09 .02 -.0061 -.2454
.0045 -.0096
.0064 -.0086
.0120 -.0104
.0158 -.0109
0189 -.0112
0065 -.0108
0098 -.0108
0127 -.0112
0179 -.0109
0231 -.0109
0049 -.0085
0110 -.0070
.0171 -.0068
.0205 -.0067
.0292 -.0062
.0173
.0161
.0158
.0147
.0134
.0033
.0026
.0033
0033
0028
0039
0031
0045
0040
0027
.0045
.0035
.0062
.0069
.0071
0065
0073
0076
0075
0075
0049
0054
0056
0056
0055
(b) Afterbody and nozzle
MACH
1.201
1.201
1.200
1.201
1 201
902
901
900
897
900
.598
.598
.600
.600
.602
NPR ALPHA CLAFT CDAFT CMAFT
.97 .01 -.0084
3.01 .02 -.0081
5.00 .02 -.0084
7.06 .02 -.0083
9.03 .02 -.0083
i. I0 .00 -.0035
2.02 .02 -.0036
3.00 .02 -.0037
4.99 .01 -.0037
7.01 .02 -.0036
1.03 .O1 -.0032
2.02 .02 -.0031
3.01 .01 -.0036
3.58 .02 -.0031
5.09 .02 -.0028
.0083
0084
0085
0085
0085
0060
0055
0055
0054
0052
0054
0051
0051
0051
0050
.0082
0079
0081
0080
0079
0032
0034
.0034
.0034
.0032
.0030
.0030
.0036
.0029
.0027
CLN
-.0012
-.0005
-.0021
-.0026
-.0029
-.0073
-.0072
-.0075
-.0072
-.0073
-.0053
-.0039
-.0033
-.0037
-.0034
CDN
.0090
.0078
.0073
.0062
.0049
-.0028
-.0028
-.0022-.0021
-.0024
-.0015
-.0020
-.0006
-.0011
-.0024
CMN
-.0037
-.0044
-.0019
-.0011
-.0008
.0033
.0040
.0042
.0040
.0042
.0019
.0024
.0021
.0027
.0028
24
Table 5. Longitudinal Aerodynamic Characteristics for A/B Nozzle With 25/25 A/B
Sidewalls and 5v,p = 0°
(a) Total aft end
MACH NPR ALPHA CLT C(D-F) CMT CL CD CM
.92
3.03
5.01
7.O0
8.97
.95
91
90
88
85
81
74
70
6.98
7.00
6.99
7. O0
7. O0
6.99
7.04
7.01
1.09
2.03
3.01
5 .O3
7.02
i. I0
1.09
1.09
1.09
1.09
1.09
1.09
1.08
5.02
5.02
5.02
5.02
5.02
5.02
5.03
5.01
.02
.02
.01
.02
.03
-2.04
.01
2.99
5.98
8.99
12.01
16.03
17.99
-1.99
-.01
3.01
6.01
9.01
11.98
15.99
18.01
-.02
-.01
-.02
.00
.00
-2.05
-.01
3.02
6.02
9.03
12.01
16.00
18.01
-2.05
.01
2.99
6.00
9.00
12.02
16.04
18.01
1.200
1.200
1.202
1.202
1.201
1.200
1.203
1.204
1.200
1.201
1 204
1 200
1 200
1 200
1 202
1 201
1 201
1.199
1.199
1.203
1.200
.901
.903
.898
.903
.899
.902
.901
.902
.897
.901
.902
901
899
901
899
900
901
901
902
903
899
-.0104
-.0092
-.0101
-.0102
-.0105
-.0222
-.0109
.0039
.0197
.0337
.0498
.0660
.0752
-.0210
-.0079
.0097
0291
0491
0670
0919
1035
- 0092
- 0089
-.0077
-.0082
-.0078
-.0080
-.0079
-.0031
-.0053
-.0027
.0140
.0290
.0376
-.0113
-.0077
.0022
.0056
.0146
.0367
.0612
.0738
.0184 .0054
-.0152 .0063
-.0448 .0106
-.0760 .0137
-.1075 .0174
.0196 .0131
.0184 .0052
.0186 -.0048
.0218 -.0176
.0294 -.0302
.0375 -.0469
.0487 -.0643
.0550 -.0745
-.0742 .0193
-.0752 .0128
-.0746 .0065
-.0717 -.0035
-.0664 -.0159
-.0576 -.0315
-.0460 -.0514
-.0392 -.0607
.0042 .0046
-.0261 .0079
-.0513 .0091
-.1044 .0147
-.1601 .0197
.0038 .OO30
.0038 .0043
.0033 .0044
.0027 .0063
.0032 .0065
.0077 -.0032
.0174 -.0144
.0249 -.0221
-.1051 .0131
-.1054 .0146
-.1055 .0144
-.1057 .0170
-.1043 .0162
-.0986 .0061
-.0862 -.0081
-.0783 -.0172
-.0104
-.0093
-.0101
-.0102
-.0106
-.0222
-.0109
0039
0198
0338
0499
0661
0753
-.0178
-.0079
.0049
.0196
.0348
.0481
.0668
.0754
-.0092
-.0089
-.0077
-.0082
-.0079
-.0080
-.0079
-.0031
-.0052
-.0027
.0141
.0291
.0378
-.0074
-.0077
-.0035
-.0058
-.0024
.0141
.0313
.0402
.0184
.0162
.0161
.0150
0136
0196
0184
0186
0218
0294
0375
0487
0551
0169
.0159
.0164
.0190
.0239
.0318
.0418
.0478
.0042
.0032
.0041
.0040
.0032
.0038
.0038
.0033
.0027
.0032
.0077
.0174
.0250
.0037
.0038
0035
0028
0033
0078
0183
0255
.0054
.0034
.0048
.0050
.0057
.0131
.O052
-.0048
-.0176
-.0302
-.0469
-.0643
-.0745
.0105
.0041
-.0022
-.0123
-.0247
-.0402
-.0602
-.0695
.0046
.0054
.0040
.0044
.0040
.0030
.0043
.0044
.0063
.0065
-.0032
-.0144
-.0221
0027
0042
0040
0066
0058
- 0042
- 0185
- 0277
25
Table 5. Continued
(a) Continued
MACH
.602
.599
.604
.597
.598
.602
.599
601
600
602
600
598
599
.600
599
602
6OO
599
599
598
6OO
598
6OO
599
.600
.599
.600
.601
.600
.601
•598
.601
.599
• 601
• 600.598
.600
.599
NPR
1.03
1.99
3. O0
3.54
4.97
1.03
1.03
1.03
1.03
1.03
1.03
1.03
1.02
3.49
3.50
3.50
3.50
3.50
3.50
3.49
3.50
1.02
1.97
3.01
3.55
4.98
1.03
1.03
1.02
1.00
.98
.96
3.49
3.51
3.51
3.51
3.52
3.51
ALPHA
.03
.02
.02
.O1
.01
-1.74
.03
2.99
6.00
8.99
12.00
15.99
17.98
-1.67
.01
3.00
6.01
9.00
12.00
16.00
17.99
20.02
20.01
19.99
20.00
20.00
16.59
17.96
19.98
23.98
27.98
31.96
16.78
17.99
19.99
23.99
27.99
31.98
CLT
-.0102
-.0079
-.0070
-.0065
-.0050
-.0057
-.0041
-.0020
.0015
.0051
.0098
.0258
.0334
-.0096
-.0033
.0069
.0186
.0308
.0440
.0703
.0838
.0410
.0624
.0843
.0957
.1263
.0268
.0318
.0397
.0569
.0773
.0932
.0710
.0804
.0937
.1229
.1551
.1834
C(D-F) CMT CL CD CM
.0048
-.0610
-.1177
-.1523
-.2385
.0049
0048
0041
0046
0052
0068
0132
0180
-.1493
-.1495
-.1487
-.1480
-.1461
-.1425
-.1343
-.1269
.0232
-.0374
-.0944
-.1248
-.2052
.0142
.0175
.0229
.0382
.0596
.0849
-.1327
-.1292
-.1229
-.1045
-.0768
-.0459
•0048
.0097
.0146
0179
0249
0030
0028
0030
0014
-.0009
-.0052
-.0180
-.0233
.0175
.0167
.0162
.0146
.0115
.0064
-.0074
-.0141
-.0288
-.0236
-.0205
-.0184
-.0125
-.0190
-.0225
-.0288
-.0460
-.0728
-.1036
-.0075
-.0117
-.0181
-.0375
-.0681
-.1029
-•0102
-.0079
-.0070
-.0065
-.0050
-.0058
-.0041
-.0020
.0016
.0052
.0099
.0259
.0336
-.0052
-.0033
-.0010
.0026
.0068
.0121
.0279
.0366
.0412
.0413
.0419
.0422
.0431
.0269
.0319
.0398
0571
0775
0934
0269
0331
0412
0601
.0829
.1017
.0048
.0029
.0044
.0047
.0054
.0049
0048
0041
0047
0052
0069
0132
0180
0039
.0040
.0040
.0046
.0056
.0077
.0138
.0188
.0233
.0211
.0226
.0226
.0237
.0142
.0175
.0229
.0383
.0597
.0850
.0140
.0169
.0221
.0371
.0594
.0854
.0048
.0042
.0033
.0031
.0017
.0030
.0028
.0030
.0014
-.0009
-.0052
-.0180
-.0233
.0031
.0023
.0018
.0002
-.0029
-.0080
-.0218
-.0285
-.0288
-.0289
-.0320
-.0331
-.0358
-.0190
-.0225
-.0288
-.0460
-.0728
-.1036
-.0219
-.0261
-.0325
-.0520
-.0826
-.1174
26
Table 5. Continued
(a) Concluded
MACH NPR ALPHA CLT C(D-F) CMT
•151 1.00 .02 .0108 .0098 -.0077
149 2.00 .01 .0270 -i.0416 .0749
151 2.59 .00 .0297 -1.5589 .1185
151 3.00 .01 .0288 -1.9362 .1658
150 3.78 .00 .0322 -2.7005 .2354
149 1.00 -1.36 .0100 .0003 -.0031
150 1.00 .00 .0274 -.0007 -.0094
149 1.00 2.99 .0333 -.0018 -.0095
151 1.00 5.98 .0363 .0003 -.0099
151 1.00 9.01 .0347 .0049 -.0108
150 1.00 12.00 .0343 .0110 -.0117
148 1.00 15.99 .0516 .0174 -.0244
151 1.00 17.98 .0550 .0231 -.0296
•150 2.59 -1.39 -.0127 -1.5848 .1245
150 2.59 -.02 .0257 -1.5878 .1239
151 2.60 3.02 .1076 -1.5731 .1258
151 2.60 5.98 .1877 -1.5526 .1249
148 2.60 9.00 .2891 -1.5993 .1254
151 2.60 11.99 .3614 -1.5196 .1182
150 2.60 15.99 .4850 -1.5058 .1096
148 2.60 17.98 .5675 -1.5380 .I040
151 1.00 19.99 .0349 .0254 -.0269
150 2.01 19.97 .3839 -.9574 .0770
150 2.60 19.98 .5841 -1.4836 .1187
150 3.01 19.98 .7095 -1.8380 .1607
150 3.84 19.98 .9838 -2.5838 .2355
149 1.00 15.98 .0092 .0158 -.0119
152 1.O0 17.97 .0252 .0182 -.0229
149 1.00 19.98 .0390 .0280 -.0298
149 1.00 23.99 .0640 .0414 -.0448
149 1.00 27.98 .0728 .0574 -.0592
.149 1.00 31.98 .0978 .0821 -.0846
.149 1.00 34.98 .1066 .1011 -.1024
.151 2.61 15.98 .4786 -1.5053 .1249
.151 2.61 17.97 .5438 -1.4827 .1140
.151 2.61 19.97 .6012 -1.4631 .1095
.151 2.61 23.97 .7145 -1.4181 .1031
.150 2.61 27.99 .8347 -1.3635 .0862
.150 2.61 31.98 .9509 -1.2870 .0630
.150 2.61 34.97 1.0279 -1.2299 .0453
CL
.0108
.0268
.0296
.0285
.0320
.0100
.0274
.0333
.0363
.0347
.0344
.0517
.0551
.0259
.0262
.0243
.0243
.0341
.0354
.0471
.0588
.0350
.0310
.0360
.0317
.0359
.0093
.0253
.0392
.0642
.0730
.0980
.1068
.0393
.0518
.0558
.0651
.0795
.0988
.1024
CD
.0098
-.0057
.0092
.0101
.0086
.0003
-.0007
-.0018
.0003
.0049
.0110
.0174
.0231
.0036
.0069
.0078
.0088
.0116
.0155
.0232
.0298
.0254
.0139
.0240
.0262
.0231
.0158
.O182
.0280
.0414
.0575
.0822
.1012
.0293
.0341
.0381
.0431
.0582
.0783
.0936
CM
-.0077
-.0140
-.0239
-.0142
-.0205
-.0031
-.0094
-.0095
-.0099
-.0108
-.0117
-.0244
-.0296
-.0196
-.0208
-.0179
-.0177
-.0226
-.0243
-.0348
-.0456
-.0269
-.0120
-.0270
-.0228
-.0268
-.0119
-.0229
-.0298
-.0448
-.0592
-.0846
-.1024
-.0202
-.0309
-.0356
-.0422
-.0601
-.0832
-.1015
27
Table 5. Continued
(b) Afterbody and nozzle
MACH
1.200
1.200
1.202
1.202
1.201
1.200
1.203
1.204
1.200
1.201
1.204
1.200
1.200
1.200
1.2021.201
1.201
1.199
1.199
1.203
1.200901
903898
903
899
902
.901
.902
.897
.901
.902
.901
.899
.901
899
900
901
901
902
903
.899
NPR ALPHA CLAFT CDAFT CMAFT
.92
3.03
5.01
7.00
8.97
.95
.91
•90
.88
.85
.81
.74
•70
6.98
7.00
6.99
7.00
7.00
6.99
7.04
7.01
1.09
2.03
3.01
5.03
7.02
I.I0
1.09
1.09
1.09
1.09
1.09
i.09
1.08
5.025.02
5.025.02
5.02
5.02
5.03
5.01
.02
.02
.01
.02
.03
-2.04
.01
2.99
5.98
8.99
12.01
16.03
17.99
-1.99
-.01
3.01
6.01
9.01
11.98
15.99
18.01
-.02
-.01
-.02
.00
.00
-2.05
-.01
3.02
6.02
9.03
12.01
16.00
18.01
-2.05
.01
2.99
6.00
9.00
12.02
16.04
18.01
-.0087
-.0085
-.0084
-.0086
-.0083
-.0171
-.0087
.0031
.0166
.0284
.0406
.0535
.0594
-.0170
-.0088
.0031
.0174
.0303
.0406
.0538
.0602
-.0034
-.0035
-.0035
-.0033
-.0034
-.0017
-.0032
-.0050
-.0054
-.0049
-.0005
.0130
.0184
-.0017
-.0033
-.0047
-.0056
-.0045
-.0003
.0145
.0203
.0083
.0083
.0084
.0084
.0084
.0091
.0085
.0090
.Oll2
.0148
.0196
.0266
.0305
.0093
.0087
.0092
.0114
.0150
.0198
0268
0309
0060
0055
0055
0054
.0052
.0059
.0059
.0059
.0056
.0058
.0072
.0139
.0184
.0053
.0054
.0053
.0050
.0052
.0067
.0139
.0184
.0084
.0082
.0080
.0082
.0079
.0153
.0082
-.0017
-.0144
-.0272
-.0418
-.0560
-.0629
.0150
•0081
-.0020
-.0155
-.0287
-.0419
-.0569
-.0640
.0028
.0030
.0029
.0027
.0028
.0010
.0026
.0052
.0061
.0070
.0053
-.0044
-.0089
.0009
.0027
.0051
.0063
.0067
.0048
-.0062
-.0119
CLN
-.0017
-.0007
-.0017
-.0017
-.0023
-.0051
-.0023
.0008
.0032
.0054
.0093
.0126
.0159
-.0008
.0008
.0018
.0022
.0045
.0075
.0130
.0151
-.0058
-.0054
-.0042
-.0049
-.0045
-.0063
-.0047
.0019
.0002
.0022
.0146
.0161
.0194
-.0058
-.0045
.0012
-.0002
.0021
.0144
.0168
.0200
CDN
.0101
.0079
.0077
.0066
.0051
.0105
.0099
.0095
.0105
.0146
.0179
.0221
.0246
.0076
.0072
.0072
.0076
.0089
.0120
.0151
.0169
-.0018
-.0023
-.0014
-.0014
-.0021
-.0021
-.0022
-.0025
-.0030
-.0026
.0005
.0034
.0065
-.0016
-.0016
-.0019
-.0023
-.0019
.0012
.0043
.0071
CMN
-.0030
-.0048
-.0032
-.0032
-.0022
-.0022
-.0031
-.0031
-.0032
-.0030
-.0051
-.0083
-.0116
-.0045
-.0041
-.0003
.0032
.0040
.0016
-.0033
-.0O55
.0018
.0024
.0010
.0017
.0012
.0020
.0017
-.0009
.0003
-.O0O4
-.0085
-.0100
-.0132
.0018
.0015
-.0011
.0003
-.0009
-.0090
-.0123
-.0157
28
Table 5. Continued
(b) Continued
MACH
.602
.599
.604
.597
.598
•602
.599
.601
.600
.602
.600
.598
.599
.600
599
602
600
599
599
598
600
598
600
599
600
599
600
•601
.600
.601
.598
.601
.599
.601
.600
.598
.600
.599
NPR ALPHA CLAFT CDAFT CMAFT
1.03
1.99
3.00
3.54
4.97
1.03
1.03
1.03
1.03
i .03
1.03
1.03
1.02
3.49
3.50
3.50
3.50
3.50
3.50
3.49
3.50
1.02
1.97
3.01
3.55
4.98
1.03
1.03
1.02
1.00
.98
.96
3.49
3.51
3.51
3.51
3.52
3.51
.03
.02
.02
.01
.01
-1.74
.03
2.99
6.00
8.99
12.00
15.99
17.98
-1.67
.01
3.00
6.01
9.00
12.00
16.00
17.99
20.02
20.01
19.99
20.00
20.00
16.59
17.96
19.98
23.98
27.98
31.96
16.78
17.99
19.99
23.99
27.99
31.98
-.0038
-.0036
-.0033
-.0033
-.0033
-.0036
-.0031
-.0020
-.0005
.0017
.0044
.0142
.0190
-.0036
-.0030
-.0018
-.0003
.0020
.0049
.0150
.0199
.0223
.0227
.0229
.0232
.0239
.0146
.0175
.0223
.0361
.0515
.0669
.0157
.0183
.0231
.0372
.0531
.0696
.0055 .0034
•0051 .0032
.0051 .0028
.0052 .0029
.0051 .0030
.0056 .0027
.0055 .0027
.0054 .0025
.0056 .0016
.0061 -.0004
.0070 -.0034
0105 -.0129
0130 -.0169
005"1 .00280051 .0027
0051 .0024
0053 .0014
0058 -.0007
0067 -.0039
0104 -.0138
0130 -.0179
0156 -.0213
0155 -.0217
0156 -.0220
0157 -.0226
0160 -.0236
.0109 -.0145
.0126 -.0168
.0156 -.0214
.0255 -.0367
.0392 -.0580
.0568 -.0841
.0110 -.0158
.0125 -.0178
.0157 -.0224
.0257 -.0383
• 0400 -.0604
.0585 -.0881
CLN
-.0064
-.0043
-.0037
-.0032
-.0017
-.0021
-.0011
.0000
.0021
.0035
.0055
.0117
.0146
-.0016
- 0003
0008
0028
0048
0072
0130
0167
0188
0185
0190
.0190
.0192
.0123
.0144
.0176
.0210
.0260
.0265
.0112
.0148
.0181
.0229
.0298
.0321
CDN
-.0007
-.0022
-.0007
-.0005
.0003
-.0006
-.0007
-.0013
-.0010
-.0009
-.0001
.0027
.0050
-.0013
-.0011
-.0011
-.0007
-.0002
.0009
.0033
.0058
.0077
.0056
.0070
.0069
.0077
.0033
.0049
.0073
.0128
.0205
.0281
.0029
.0044
.0064
.0114
.0194
.0269
CMN
.0014
.0010
.0005
.0002
-.0013
.0002
.0000
.0005
-.0002
-.0005
-.0018
-.0051
-.0065
.0003
-.0004
-.0006
-.0012
-.0022
-.0040
-.0081
-.0106
-.0075
-.0071
-.0100
-.O105
-.0122
-.0045
-.0057
-.0074
-.0093-.0149
-.0195
-.0061
-.0083
-.0101
-.0137
-.0221
-.0293
29
Table 5. Concluded
MACH
.151
.149
.151
.151
.150
.149
.150
.149
.151
.151
.150
.148
.151
.150
.150
.151
.151
.148
.151
.150
.148
.151
150
150
150
150
149
152
149
149
149
149
149
151
.151
.151
.151
.150
.150
.150
(b) Concluded
NPR ALPHA CLAFT CDAFT CMAFT
02
Ol
00
01
00
-I 36
O0
2 99
5 98
90l
12 O0
15 99
17.98
-1.39
-.02
3.02
5.98
9.00
11.99
15.99
17.98
19.99
19.97
19.98
19.98
19.98
15.98
17.97
19.98
23.99
27.98
31.98
34.98
15.98
17.97
19.97
23.97
27.99
31.98
34.97
- 0004
- 0009
- 0006
- 0007
- 0005
- 0006
- 0004
- 0005
0004
0050
0089
0136
0193
- 0030
-.0020
-.0017
0007
0028
0038
0106
0160
0196
0176
0188
0185
0190
0119
0160
0191
0285
0392
0527
0590
0111
0169
0212
0281
0383
0518
0575
i .00
2.O0
2.59
3.O0
3.78
i .00
1 O0
1 O0
1 O0
1 O0
1 O0
1 O0
1 O0
2 59
2 59
2 60
2 60
2 60
2.60
2.60
2 60
1 O0
20l
2 60
3 01
3 84
1 00
1 00
1 00
1 00
1 O0
1 00
1 00
2 61
2 61
2 61
2 61
2 61
2 61
2 61
0059 -.0010
0068 .0003
0068 .0006
0068 .0009
0070 .0009
0049 .0007
0047 -.0004
0046 .0013
0048 .0016
0055 -.OO31
0073 -.0075
0095 -.0123
0121 -.0178
0063 .0038
0062 .0030
0062 .0031
0064 .0012
0069 -.0008
.0076 -.0014
.0103 -.0091
0128 -.0146
0144 -.0219
0144 -.0202
0148 -.0216
0149 -.0215
0156 -.0225
.0109 -.0152
.0124 -.0188
.0142 -.0208
.0207 -.0300
.0303 -.0432
.0441 -.0627
.0534 -.0742
.0104 -.0111
.0124 -.0182
.0149 -.0222
.0205 -.0287
.0300 -.0407
.0441 -.0610
.0533 -.0714
CLN
0111
0277
0302
0293
0325
0106
0278
0338
0360
0298
0255
0381
0359
0289
0283
0259
0236
0313
0316
0365
0428
0154
0134
0172
0132
0169
-.0027
0092
0200
0357
0337
0453
0479
0281
0350
0346
0371
.0412
.0470
.0449
CDN
.0038
-.0125
.0023
.0033
.0017
-.0046
-.0054
-.0064
-.0045
-.0006
.0037
.0078
.0110
-.0027
.0007
.0016
.0024
.0047
.0079
.0129
.0169
.0109
-.0005
.0092
0114
0076
0049
0059
0138
0207
.0272
.0380
.0477
.0189
.0217
.0232
.0226
.0282
.0342
.0403
CMN
-.0067
-.0143
-.0244
-.0151
-.0214
-.0038
-.0091
-.0108
-.0115
-.0077
-.0042
-.0121
-.0118
-.0234
-.0238
-.0211
-.0188
-.0219
-.0228
-.0256
-.0310
-.0049
.0082
-.O053
-.0013
-.0043
.0033
-.0041
-.0090
-.0148
-.0160
-.0219
-.0283
-.0090
-.0127
-.0134
-.0135
-.0194
-.0222
-.0301
3O
Table 6. Longitudinal Aerodynamic Characteristics for A/B Nozzle With 100/100
Dry Sidewalls and 5v,p = 0 °
(a) Total aft end
MACH NPR ALPHA CLT C(D-F) CMT CL CD CM
1.202 .97 .00 -.0091 .0168 .0039 -.0091 .0168 .0039
1.201 3.01 .01 -.0094 -.0151 .0069 -.0095 .0161 .0038
1.200 4.94 .02 -.0113 -.0445 .0122 -.0113 .0158 .0063
1.200 7.01 .03 -.0121 -.0774 .0164 -.0122 .0137 .0075
1.201 9.04 .02 -.0116 -.1089 .0192 -.0117 .0123 .0073
•904 I.I0 -.02 -.0106 .0033 .0063 -.0106 .0033 .0063
•896 2.01 .02 -.0095 -.0263 .0086 -.0095 .0031 .0057
•897 3.00 .02 -.0102 -.0520 .0124 -.0102 .0039 .0069
•900 5.00 .01 -.0099 -.1056 .0175 -.0099 .0030 .0068
•902 7.01 .02 -.0099 -.1596 .0228 -.0099 .0014 .0071
•601 1.03 -.03 -.0056 .0038 .0041 -.0056 .0038 .0041
.600 1.99 .01 -.0038 -.0605 .0091 -.0039 .0037 .0027
•600 3.03 .01 -.0046 -.1211 .0163 -.0046 .0050 .0038
•601 3.50 .01 -.0045 -.1496 .0190 -.0045 .0048 .0038
•599 4.99 .00 -.0037 -.2406 .0275 -.0037 .0041 .0036
•601 1.03 -1.81 -.0051 .0042 .0036 -.0052 .0042 .0036
•600 1.03 2.02 -.0017 .0038 .0032 -.0017 .0038 .0032
•599 1.03 -.01 -.0038 .0037 .0036 -.0038 .0037 .0036
•598 1.03 6.00 .0010 .0039 .0022 .0010 .0039 .0022
•601 1.03 8.97 .0054 .0049 -.0009 .0055 .0049 -.0009
•602 1.03 11.98 .0109 .0067 -.0060 .0110 .0067 -.0060
31
Table 6. Concluded
(b) Afterbody and nozzle
MACH
1.202
1.201
1.200
1.200
1.201
.904
.896
.897
90O
902
601
600
600
601
599
601
600
599
598
601
602
NPR ALPHA CLAFT CDAFT CMAFT
.97
3.01
4.94
7.01
9.04
i.I0
2.01
3.O0
5.00
7.01
1.03
1.99
3.03
3.50
4.99
1.03
1.03
1.03
1.03
1.03
1.03
.O0
.01
.02
.03
.02
-.02
.02
.02
.01
.02
-.03
.01
.01
.01
.O0
-1.81
2.02
-.01
6.00
8.97
11.98
-.0084
-.0083
-.0084
-.0085
-.0084
-.0036
-.0038
-.0038
-.0037
-.0036
-.0033
-.0031
-.0031
-.0031
-.0025
-.0035
-.0023
-.0031
--.0003
.0019
.0048
.0084
.0084
.0085
.0085
.0085
.0060
.0054
.0055
.0054
.0051
.0053
.0050
.0050
.0050
.0050
.0053
.0052
.0052
.0054
.0059
.0068
.0081
.0080
.0080
.0080
.0080
.0032
.0035
.0034
.0033
.0032
0031
0028
0030
0029
0022
0028
0027
0029
.0015
-.0005
-.0038
CLN
-.0007
-.0011
-.0029
-.0037
-.0033
-.0071
-.0056
-.0064
-.0062
-.0064
-.0023
-.0008
-.0015
-.0015
-.0012
-.0016
.0006
-.0007
.0013
.0036
.0062
CDN
.0085
.0077
.0074
.0052
.0038
-.0027
-.0023
-.0016
-.0023
-.0037
-.0015
-.0012
.0000
-.0002
-.0009
-.0011
-.0014
-.0015
-.0016
-.0010
-.0001
CMN
-.0042
-.0042
-.0017
-.0005
-.0006
.0031
.0022
.0035
.0035
.0039
.0010
-.0002
.0008
.0009
.0013
.0009
.0005
.0007
.0007
-.0004
-.0022
32
Table 7. Longitudinal Aerodynamic Characteristics for A/B Nozzle With 100/100
A/B Sidewalls and 6v,p = 15°
MACH NPR ALPHA CLT C(D-F) CMT CL CD CM
1.205
1.199
1.197
1.197
1.202
1.197
1.195
1.200
1.198
1.197
1.201
1.199
1.202
1.200
1.202
1 2O0
1 2O0
1 199
9OO
9OO
9OO
.899
.899
.901
.901
.899
.899
.899
.903
.898
.902
.902
.898
.902
.899
.898
.900
.902
.896
.93
3.00
5.00
6.98
8.91
.96
91
89
85
8O
73
66
62
7.01
7.04
6.98
6.99
7.06
1.06
2.00
3.01
5.01
6.98
1.07
1.06
1.06
1.06
1.06
1.06
1.03
1.01
5.02
4.99
5.01
4.99
4.98
5.01
5.02
4.99
.03
.02
.00
-.03
-.01
-2.01
-.03
3.03
5.99
9.02
12.00
16.00
17.99
-1.98
.03
2.99
8.99
11.98
-.02
.01
-.01
-.03
-.04
-2.01
.00
3.02
6.03
9.02
12.00
16.01
18.00
-2.02
.00
3.00
6.00
8.98
12.00
16.00
17.97
-.0065
.0086
.0214
.0312
.0385
-.0187
-.0080
.0081
.0260
.0397
.0575
.0740
0851
0202
0333
0506
0853
1024
.0021
0185
0275
0448
0600
0024
0035
0073
0053
.0104
.0262
.0437
.0504
.0399
.0446
.0542
.0575
.0701
.0880
.I153
.1250
.0161
-.0121
-.0404
-.0693
-.0970
.0173
.0169
.0190
.0242
.0317
.0417
.0537
.0609
-.0700
-.0694
-.0656
-.0517
-.0435
.0049
-.0208
-.0448
-.0953
-.1452
.0045
.0050
.0052
.0055
.0073
.0128
.0251
.0328
-.0961
-.0950
-.0920
-.0892
-.0845
-.0761
-.0581
-.0498
.0007
-.0245
-.0439
-.0583
-.0682
.0083
.0012
-.0116
-.0288
-.0423
-.0635
-.0844
-.0979
-.0533
-.0593
-.0668
-.0885
- 1023
- 0133
- 0390
- 0532
- 0788
- I000
-.0142
-.0140
-.0142
-.0131
-.0175
-.0278
-.0437
-.0487
-.0788
-.0786
-.0795
-.0785
-.0831
-.0928
-.1109
-.1199
-.0065
-.0009
.0045
.0071
.0074
-.0187
-.0080
.0081
.0260
.0397
.0576
.0741
.0853
-.0010
.0090
.0222
.0484
0608
0021
0089
0107
0149
0173
0024
.0035
.0073
.0054
.0104
.0263
.0439
.0505
.0136
.0148
.0193
.0174
.0249
.0379
.0589
.0654
.0161 .0007
.0163 -.0101
.0164 -.0195
.0158 -.0239
.0146 -.0244
.0173 .0083
.0169 .0012
.0190 -.0116
.0242 -.0288
0317 -.0423
0417 -.0635
0537 -.0844
0610 -.0979
0158 -.0189
0158 -.0249
0176 -.0326
.0282 -.0542
.0355 -.0676
.0049 -.0133
.0050 -.0242
.0057 -.0276
.0057 -.0354
.0056 -.0389
.0045 -.0142
.0050 -.0140
.0052 -.0142
.0055 -.0131
.0073 -.0175
.0128 -.0278
.0251 -.0437
.0328 -.0487
.0053 -.0356
.0057 -.0353
.0067 -.0364
.0077 -.0352
.0103 -.0397
.0163 -.0494
.0304 -.0676
.0372 -.0763
33
Table 7. Continued
MACH
.600
.602
.601
.601
600
597
600
601
602
600
602
601
599
602
601
.602
602
602
601
602
601
599
599
599
598
599
599
601
601
598
6O0
600
598
602
600
599
60O
599
NPR
1.02
1.99
2.99
3.52
5.02
I. 04
1.02
1 02
I Ol
10l
10l
I O0
99
3 54
3 50
3.50
3.50
3.49
3.49
3.49
.99
.98
2.02
3. O0
3.54
5.03
3.48
1.00
.98
.97
.95
.93
3.53
3.54
3.54
3.53
3.54
3.54
ALPHA
.02
.01
-.04
-.05
-.05
-2.12
-.03
3.01
6.02
8.97
12.01
16.02
17.98
-2.04
.02
3.02
5.98
8.99
12.00
16.01
18.01
20.01
19.97
19.98
19.99
19.97
18.01
16.49
19.98
23.97
27.99
31.98
16.10
17.98
19.98
23.96
27.98
31.97
CLT
.0063
.0395
.0567
.0659
.0905
0066
0101
0140
0186
0224
0283
0439
0521
0613
0678
0786
0899
.1017
.1136
.1391
.0477
.0567
.1082
.1425
.1617
.2143
.1531
.0423
.0560
.0722
.0904
.1055
.1376
.1494
.1615
.1897
.2113
.2362
C(D-F) CMT CL CD CM
0059
- 0506
- 1054
- 1353
- 2203
0049
0055
0067
0090
0114
0147
.0230
.0287
-.1383
-.1339
-.1289
-.1235
-.1171
-.1098
-.0946
.0268
.0336
-.0110
-.0565
-.0821
-.1521
-.0860
.0229
.0333
.0498
.0700
.0958
-.1006
-.0900
-.0809
-.0562
-.0295
.0072
-.0195
-.0684
-.0928
-.1061
-.1419
-.0200
-.0211
-.0228
-.0262
-.0301
-.0362
-.0499
-.0563
-.1059
-.1065
-.1087
-.1125
-.1173
-.1236
-.1393
-.0549
-.0615
-.1160
-.1403
-.1546
-.1915
-.1478
-.0507
-.0620
-.0795
-.1014
-.1316
-.1413
-.1470
-.1544
-.1764
-.1961
-.2330
.0063
.0183
0193
0208
0233
0066
0101
0140
0186
0225
0284
0440
0522
0209
0228
0266
.0308
.0357
.0407
.0577
.0478
.0568
.0673
.0681
.0694
.0727
.0668
.0424
.0561
.0724
.0906
.1058
.0535
.0624
.0699
.0896
.1038
.1213
OO59
0066
0069
0068
0071
0049
0055
0067
0090
0114
0147
.0230
.0287
.0061
.0069
.0086
.0111
.0140
.0180
.0275
.0268
.0336
.0374
.0376
.0378
.0395
.0341
.0229
.0333
.0499
.0700
.0959
.0255
.0317
.0382
.0566
.0759
.1052
-.0195
-.0354
-.0360
-.0385
-.0442
-.0200
-.0211
-.0228
-.0262
-.0301
-.0362
-.0499
-.0563
-.0381
-.0394
-.0419
-.0457
-.0506
-.0567
-.0725
-.0549
-.0615
-.0818
-.0828
-.0861
-.0933
-.0805
-.0507
-.0620
-.0795
-.1014
-.1316
-.0727
-.0793
-.0864
-.1081
-.1280
-.1646
34
Table 7. Concluded
MACH
•152
.153
.150
.150
.149
.152
•152
.153
152
152
152
151
154
153
152
152
152
151
151
151
155
151
152
152
152
152
152
152
152
150
149
149
151
151
150
151
.150
•150
.150
NPR
1.00
2•01
2.60
2.98
i.00
I.00
i.00
1.00
1.00
1.00
1.00
1.00
2.59
2.60
2.60
2.60
2.60
2.60
2.60
2.60
i.O0
2.02
2.61
2.99
3.83
1.O0
1.00
1.00
1.00
I.O0
1.00
1.00
2.62
2.60
2.59
2.59
2.59
2.59
2.59
ALPHA
-.02
-.03
-.02
-.02
-1.90
.01
3.00
6.03
8.99
11.99
16.02
17.93
-2.03
-.01
2.98
5.98
9.03
11.95
15.92
17.55
20.01
19.97
19.96
19.98
19.96
15.98
17.98
19.98
23.98
27.99
31.98
35.18
15.97
17.99
19.96
23.97
27.97
31.97
34.98
CLT C(D-F) CMT
-.0225 -.0116
.3415 -.9091
.5170 -1.4535
.5951 -1.7745
0272 -.0023
0167 -.0029
0225 -.0019
0201 -•0016
0289 .0039
0315 .0106
0407 .0166
0406 .0201
.4535 -1.3913
.5103 -1.3795
.5946 -1.3851
.6703 -1.3490
.7468 -1.3106
.8229 -1.2705
.9291 -1.2101
.9714 -1.1832
.0528 .0283
.7021 -.7146
1.0236 -1.1245
1•2146 -1.4097
1•6433 -2.0324
.0259 .0236
.0435 .0325
.0560 0412
.0711 0564
.0942 0799
.1157 1085
.1164 1231
.9573 -I 2009
.9989 -1.1471
1.0530 -1.1068
1.1293 -1.0273
1.2273 -.9397
1.3133 -.8512
1•3705 -.7700
-.0065
-.5587
-.8291
-.9299
-.0255
-.0205
-.0219
-.0219
-.0279
-.0316
-.0451
-.0495
-.7918
-.7968
-.8158
-•8186
-•8232
-.8336
-.8516
-.8622
-.0520
-.6093
-.8559
-.9647
-1.2419
-.0428
-.0553
-.0630
-•0738
-.0964
-.1212
-.1340
-.8685
-.8727
-.8830
-.8827
-.9049
-.9325
-.9499
CL
-.0225
.0078
.0075
-.0011
.0272
.0167
.0225
.0201
.0289
.0316
.0408
.0407
.0182
0244
0234
0269
0316
0379
0526
0561
0530
0619
0632
0610
0638
0260
.0436
0561
0713
0944
1160
1166
0657
0744
0860
0840
.1027
.1069
.1160
CD
-.0116
-•0074
.0060
.0150
-.0023
-.0029
-.0019
-.0016
0039
0107
0166
0201
0094
0098
0106
0143
0174
0244
0325
0392
0283
0405
0525
0456
0415
0237
0325
.0412
.0564
.0799
.1086
.1232
.0640
.0684
.0762
.0831
.0995
.1169
.1328
CM
-.O065
-.0388
-.0399
-.0229
-.0255
-.0205
-.0219
-.0219
-.0279
-.0316
-.0451
-.0495
-.0418
- 0447
- 0454- 0484
- 0527
- 0600
- 0747
- 0821
- 0520
-.0743
-.0813
-•0730
-.0922
-.0428
-.0553
-.0630
-.0738
-.0964
-.1212
-.1340
-.0816
-.0929
-.I011
-.1027
-.1220
-.1419
-.1598
35
Table 8. Longitudinal Aerodynamic Characteristics for A/B Nozzle With 50/50 A/BSidewalls and _v,p = 15 °
(a) Total aft end
MACH
1.199
1.200
1.200
1.194
1.200
.899
.904
.901
.899
.901
.601
.601
.601
.601
.601
NPR ALPHA CLT C(D-F) CMT CL CD CM
•91 .02 -.0076 .0181 .0030 -.0076 .0181 .0030
3.02 -.02 .0084 -.0110 -.0227 -.0010 .0177 -.0087
4.97 -.02 .0217 -.0379 -.0433 .0052 .0181 -.0194
6.96 -.02 .0331 -.0673 -.0599 .0090 .0175 -.0254
9.02 -.03 .0411 -.0963 -.0708 .0098 .0165 -.0263
1.06 -.03 -.0003 .0059 -.0099 -.0003 .0059 -.0099
2.04 .01 .0135 -.0215 -.0311 .0050 .0054 -.0186
2.99 -.02 .0250 -.0438 -.0488 .0086 .0061 -.0243
5.04 -.04 .0451 -.0945 -.0782 .0153 .0068 -.0350
7.02 -.04 .0604 -.1437 -.1002 .0178 .0068 -.0392
1.02 .03 .0079 .0067 -.0180 .0079 .0067 -.0180
2.00 -.03 .0344 -.0520 -.0573 .0159 .0067 -.0305
3.04 -.03 .0564 -.1075 -.0904 .0187 .0077 -.0343
3.52 -.03 .0655 -.1338 -.1032 .0207 .0081 -.0373
5.05 -.03 .0919 -.2186 -.1418 .0250 .0089 -.0449
(b) Afterbody and nozzle
MACH
1.199
1.200
1.200
1.194
1.200
.899
.904
901
899
901
601
601
601
601
.601
NPR ALPHA CLAFT CDAFT CMAFT CLN CDN CMN
.91 .02 -.0080 .0086 .0078 .0004 .0094 -.0047
3.02 -.02 -.0067 .0087 .0064 .0057 .0089 -.0152
4.97 -.02 -.0055 .0087 .0053 .0107 .0094 -.0246
6.96 -.02 -.0044 .0087 .0041 .0134 .0088 -.0295
9.02 -.03 -.0035 .0086 .0030 .0133 .0079 -.0293
1.06 -.03 -.0011 .0056 -.0007 .0008 .0003 -.0092
2.04 .01 .0006 .0050 -.0032 .0044 .0004 -.0154
2.99 -.02 .0014 .0049 -.0044 .0072 .0011 -.0199
5.04 -.04 .0030 .0048 -.0066 .0123 .0020 -.0284
7.02 -.04 .0040 .0046 -.0081 .0138 .0022 -.0311
1.02 .03 .0015 .0051 -.0040 .0064 .0016 -.0140
2.00 -.03 .0039 .0048 -.0073 .0120 .0020 -.0232
3.04 -.03 .0049 .0048 -.0087 .0138 .0029 -.0256
3.52 -.03 .0055 .0048 -.0096 .0152 .0033 -.0277
5.05 -.03 .0071 .0048 -.0117 .0179 .0040 -.0332
36
Table 9. Longitudinal Aerodynamic Characteristics for A/B Nozzle With 25/25 A/B
Sidewalls and 6v,p = 15 °
(a) Total aft end
HACH NPR ALPHA CLT C(D-F) CMT CL CD CM
1.200
1.200
1.201
1.201
1.200
1.199
1.202
1.200
1.198
1.201
1.203
1.200
1.203
1.200
1.198
1.199
1.200
1.199
1.199
.901
.898
.901
.901
.900
.899
.902
.899
.902
.903
.900
.899
.898
.901
.900
900
900
898
898
898
899
.91
3.02
5.04
7.04
9.01
.93
90
88
86
80
74
64
61
7 02
7 O0
70l
7 02
7.02
7.02
1.07
2.03
3.00
5.01
7.04
1.07
1.07
1.06
1.06
1.07
1.06
1.03
!.01
5.03
5.01
5.00
5.00
4.99
4.99
4.99
5. O0
.00
.00
-.02
-.04
-.03
-2.02
-.03
3.01
6.00
9 02
12 02
16 Ol
18 O0
-2 02
O0
3 02
6 O0
8.98
11.99
-.02
-.02
-.03
-.03
-.04
-2.01
.02
3.01
6.00
8.99
12.02
16.03
18.00
-2.04
.01
2.97
5.99
8.99
11.99
15.98
18.00
-.0060
.0079
.0219
.0334
.0420
-.0178
-.0070
0091
0275
0412
0589
0780
0894
0208
.0337
.0519
.0727
.0888
.1070
.0018
.0120
.0256
.0463
.0639
.0009
.0003
.0062
.0040
.0098
.0258
.0436
.0521
.0406
.0449
.0546
.0569
.0701
.0891
.1179
.1284
.0168
-.0119
-.0396
-.0681
-.0971
0174
0171
0195
0240
0317
0413
0543
0621
- 0684
- 0674
- 0646
- 0591
-.0501
-.0403
.0051
-.0230
-.0447
-.0936
-.1444
.0048
.0051
.0052
.0051
.0069
.0127
.0254
.0332
-.0958
-.0941
-.0913
-.0888
-.0840
-.0752
-.0572
-.0472
.0003 -.0060
-.0217 -.0010
-.0439 .0055
-.0615 .0096
-.0735 .0107
.0083 -.0178
.0007 -.0070
-.0116 .0092
-.0276 .0276
-.0401 .0413
-.0610 .0590
-.0834 .0781
-.0976 .0895
-.0561 -.0001
-.0620 .0099
-.0695 .0237
-.0817 .0401
-.0921 .0520
-.1073 .0660
-.0090 .0018
-.0243 .0039
-.0462 .0100
-.0782 .0174
-.1040 .0214
-.0096 .0008
-.0086 .0003
-.0103 .0062
-.0081 .0040
-.0136 .0099
-.0240 .0259
-.0393 .0437
-.0463 .0522
-.0784 .0151
-.0778 .0159
-.0790 .0204
-.0768 .0177
-.0818 .0257
-.0927 .0399
-.1126 .0623
-.1210 .0699
.0168
0168
0174
0170
0157
0174
0171
0195
0240
0317
0413
.0543
.0622
.0173
.0174
.0188
.0229
.0301
.0379
.0051
.0044
.0057
.0070
.0071
.0048
.0051
.0052
.0051
.0069
.0127
.0254
.0333
.0061
.0066
.0075
.0081
.0109
.0172
.0316
.0395
.0003
-.0089
-.0201
-.0269
-.0282
.0083
.0007
-.0116
-.0276
-.0401
-.0610
-.0834
-.0976
-.0216
-.0275
-.0349
-.0471
-.0575
-.0727
-.0090
-.0129
-.0238
-.0362
-.0424
-.0096
-.0086
-.0103
-.0081
-.0136
-.0240
-.0393
-.0463
-.0363
- 0358
- 0371
- 0349
- 0398
- 0507
- 0706
- 0790
37
Table 9. Continued
(a) Continued
MACH
•6O0
.601
.600
•600
.601
600
598
600
600
603
600
599
601
598
600
603
601
601
600
600
597
601
599
600
600
599
600
599
597
600
601
600
598
601
598
600
600
601
NPR
1.02
1.99
3.00
3.50
5.01
1.03
1.02
1.02
1.02
1.01
1.01
I.O0
.99
3.49
3.52
3.52
3.51
3.51
3.51
3.51
3.50
.98
2.03
3.01
3.51
5.O0
1.00
.99
.98
.97
.95
.92
3.49
3.50
3.49
3.49
3.49
3.50
ALPHA
.01
-.04
-.03
-.04
-.04
-2.02
-.02
2.99
5.99
9.02
12.00
15.99
18.01
-2.04
-.02
3.00
6.01
8.98
12.00
15.99
17.96
20.00
19.97
19.95
19.96
19.95
16.52
17.97
19.96
23.97
27.96
31.96
16.15
17.95
19.97
23.98
27.95
31.97
CLT
.0067
.0273
.0528
.0623
.0911
.0060
.0097
.0121
.0165
.0215
.0266
.0420
.0502
.0572
.0644
.0748
.0862
.0981
.1105
.1371
.1514
.0543
.0989
.1370
.1565
.2120
.0392
.0446
.0519
.0701
.0885
1065
1312
1431
1557
1834
2075
2333
C(D-F) CMT CL CD CM
.0057
-.0544
-.1076
-.1344
-.2165
.0053
.0056
.0067
.0085
.0109
.0137
.0221
.0280
- 1366
- 1351
- 1302
- 1257
- 1200
- 1126
-.0978
-.0896
.0326
-.0179
-.0596
-.0820
-.1488
.0219
.0256
.0317
.0487
.0691
.0964
-.0999
-.0903
-.0817
-.0564
-.0282
.0098
-.0167
-.0448
-.0838
-.0982
-.1409
-.0163
-.0177
-.0185
-.0218
-.0261
-.0315
-.0447
-.0512
-.0976
-.0994
- 1010
- 1047
- 1096
- 1160
- 1326
- 1413
-.0557
-.0960
-.1293
-.1456
-.1902
-.0452
-.0492
-.0555
-.0752
-.0995
-.1343
-.1310
-.1373
-.1453
-.1683
-.1926
-.2326
.0067
.0101
.0176
.0198
.0263
.0060
.0097
.0121
.0166
.0216
.0267
.0421
.0503
.0194
.0215
.0249
.0290
.0339
.0392
.0570
.0665
.0544
.0611
.0648
.0676
.0734
.0394
.0448
.O520
.0702
.0887
.1067
.0506
.0595
.0674
.0875
.1040
.1231
.0057
.0045
.0067
.0065
.0088
.0053
.0056
.0067
.0085
.0109
.0137
.0221
.0280
.0064
.0075
.0088
.0108
.0134
.0174
.0268
.0328
.0326
.0334
.0361
.0374
.0420
.0219
.0256
.0317
.0487
.0692
.0965
.0244
.0303
.0366
.0550
.0763
.1066
-.0167
-.0209
-.0329
-.0366
-.0469
-.0163
-.0177
-.0185
-.0218
-.0261
-.0315
-.0447
-.0512
-.0357
-.0374
-.0395
-.0431
-.0479
-.0542
-.0708
-.0790
-.0557
-.0707
-.0783
-.0836
-.0956
-.0452
-.0492
-.0555
-.0752
-.0995
-.1343
-.0690
-.0759
-.0835
-.1068
-.1310
-.1712
38
Table 9. Continued
MACH
150
151
151
151
150
152
.150
151
150
151
151
150
151
150
150
151
150
.150
150
149
149
149
149
152
.153
.148
149
152
149
150
147
148
151
149
149
.148
.151
.151
.151
•150
NPR
1.00
2.01
2.60
3.04
3.76
1.00
I. O0
I. O0
I. O0
I. O0
1.00
1.00
I. O0
2.61
2.62
2.62
2.61
2.61
2.62
2.61
2.61
1.00
2.01
2.63
3.01
3.80
I. O0
1.00
1.00
i. O0
1.00
1.00
I. O0
2.59
2.59
2.59
2.59
2.59
2.59
2.59
ALPHA CLT
(a) Concluded
C(D-F) CMT CL CD CM
•01 .0381 .0067 -.0327
-.03 .3226 -.9357 -.4342
-.03 .5032 -1.4329 -.7190
-.01 .5978 -1.8054 -.8609
•00 .7907 -2.4841 -1.1401
-1.59 .0037 .0039 -.0187
-.01 .0069 .0021 -.0176
3.00 .0094 .0036 -.0196
6.00 .0100 .0022 -.0192
8.99 .0265 .0204 -.0290
11.99 .0318 .0253 -.0333
16.01 .0454 .0338 -.0459
18.00 .0570 .0415 -.0570
-1.96 .4407 -1.4704 -.7199
-.03 .4888 -1.4546 -.7189
3.00 .5685 -1.4201 -.7168
5.99 .6488 -1.3950 -.7221
8.99 .7235 -1.3563 -.7258
12.00 .8115 -1.3211 -.7373
15.98 .9226 -1.2663 -.7595
17.86 .9750 -1.2313 -.7691
20.02 .0456 .0299 -.0483
19.99 .6358 -.7864 -.4466
19.97 .9586 -1.1737 -.7178
19.96 1.1527 -1.4304 -.8519
19.96 1.6637 -2.1388 -1.2027
15.98 .0164 .0196 -.0349
17.96 .0288 .0227 -.0458
19.97 .0395 .0303 -.0512
23.98 .0627 .0452 -.0664
27.97 .0822 .0643 -.0871
31.96 .1044 .0921 -.1149
34.98 .1124 .1085 -.1321
15.97 .9017 -1.2614 -.7492
17.97 .9496 -1.2232 -.7563
19.97 1.0036 -1.1961 -.7635
23.97 1.0624 -1.0811 -.7481
27.98 1.1614 -.9947 -.7687
31.97 1.2535 -.8971 -.7965
34.96 1.3192 -.8259 -.8207
.0381
.0426
.0416
.0340
.0446
.0037
.0069
.0095
.0100
.0265
.0319
.0455
.0572
.0228
.0211
.0260
.0289
.0292
.0415
.0519
.0601
.0457
.0359
.0313
.0418
.0456
.0165
.0289
.0397
0629
0824
1046
1126
0367
0424
.0459
.O548
.0746
.0921
.0989
0067
0145
0297
0265
0188
0039
0021
0036
0022
.0204
0253
0339
0415
0292
0289
0290
0294
.0349
.0387
.0490
.0568
.0300
.0270
.0358
.0385
.0459
.0197
.0227
.0304
.0453
.0644
.0922
.1086
.0444
.0474
.0507
.0570
.0722
.0943
.II01
0327
0446
0520
0462
0615
0187
0176
0196
0192
0290
0333
0459
0570
0434
0433
0446
0472
0503
0585
0741
0827
0483
0494
0562
0680
0818
0349
0458
O512
0664
O871
1149
1321
0675
0768
0791
0866
1060
1320
1515
39
Table 9. Continued
(b) Afterbody and nozzle
MACH
1.200
1.200
1.201
1.201
1.200
1.199
1.202
1.200
1.198
1.201
1.203
1.200
1.203
1.200
1.198
1.199
1.200
1.199
1.199
.901
.898
.901
.901
.900
.899
.902
.899
.902
.903
.900
.899
.898
901
9O0
900
9O0
898
898
898
899
NPR ALPHA CLAFT CDAFT CMAFT
.91
3.02
5.04
7.04
9.01
.93
90
88
86
80
74
64
61
7.02
7.00
7.01
7.02
7.02
7.02
1.07
2.03
3.00
5.01
7.04
1.07
1.07
1.06
1.06
1.07
1.06
1.03
1.01
5.03
5.01
5.O0
5.00
4.99
4.99
4.99
5.00
.00
.00
-.02
-.04
-.03
-2.02
-.03
3.01
6.00
9.02
12.02
16.01
18.00
-2.02
.00
3.02
6.00
8.98
11.99
-.02
-.02
-.03
-.03
-.04
-2.01
.02
3.01
6.00
8.99
12.02
16.03
18.00
-2.04
.01
2.97
5.99
8.99
11.99
15.98
18.00
-.0083
-.0071
-.0060
-.0048
-.0037
-.0166
-.0081
.0046
.0191
.0303
.0421
.0546
.0617
-.0130
-.0044
0081
0222
0324
0434
- 0013
- 0001
0013
0030
0042
0001
-.0012
-.0024
-.0036
-.0019
.0031
.0181
.0227
.0044
.0029
.0020
.0014
.0037
.0097
.0243
.0295
.0084 .0081
.0085 .0068
.0085 .0057
0085 .0045
0084 .0032
0092 .0149
0086 .0077
0092 -.0031
0115 -.0167
0154 -.0298
0201 -.0435
0269 -.0572
.0312 -.0660
.0091 .0113
.0087 .0040
0095 -.0067
0119 -.0201
0160 -.0321
0206 -.0446
0055 -.0004
0050 -.0021
0049 -.0043
0047 -.0067
0044 -.0084
0054 -.0019
.0055 -.0005
.0056 .0012
.0054 .0028
.0057 .0027
.0076 .0002
.0151 -.0110
.0193 -.0150
.0045 -.0084
.0048 -.0066
.0050 -.0052
.0051 -.0041
.0058 -.0041
.0084 -.0081
.0162 -.0196
.0209 -.0248
CLN
.0024
.0061
.0115
.0144
.O144
-.0012
.0011
.0046
.0085
0110
0169
0236
0277
0130
0143
0156
0179
0196
0227
0031
0040
.0087
.0144
.0172
.0008
.0015
.0085
.0076
.0118
.0228
.0256
.0295
.0106
.0129
.0184
.0163
.0220
.0302
.0381
.0404
CDN
.0084
.0083
0088
0085
0073
0082
0085
0103
0125
0163
.0212
0274
0310
0082
0087
0093
0109
0141
0173
- 0004
- 0006
0008
.0023
.0027
-.0006
-.0004
-.0004
-.0003
.0012
.0051
.0103
.0140
.0017
.0018
.OO25
.0030
.0051
.0088
.0154
.0186
CMN
-.0078
-.0157
-.0258
-.0314
-.0314
-.0067
-.0070
-.0085
-.0109
-.0104
-.0175
-.0262
-.0316
-.0329
-.0315
-.0282
-.0269
-.0254
-.0280
-.0086
-.0108
-.0195
-.0295
-.0340
-.0077
-.0080
-.0115
-.0109
-.0163
-.0242
-.0283
-.0313
-.0279
-.0292
-.0319
-.0308
-.0357
-.0426
-.0510
-.0542
4O
Table 9. Continued
(b) Continued
MACH
•600
•601
.600
•600
.601
600
598
600
600
603
600
599
601
598
600
.603
.601
.601
.600
.600
597
601
599
600
600
599
600
599
597
.600
.601
.600
.598
.601
.598
•600
.600
.601
NPR
1.02
1.99
3.00
3.50
5.01
1.03
1.02
1.02
1.02
1.01
1.01
I. O0
.99
3.49
3.52
3.52
3.51
3.51
3.51
3.51
3.50
.98
2.03
3.01
3.51
5.00
1.00
.99
.98
.97
.95
.92
3.49
3.50
3.49
3.49
3.49
3.50
ALPHA
.01
-.04
-.03
-.04
-.04
-2.02
-•02
2.99
5.99
9.02
12.00
15.99
18.01
-2.04
-.02
3.00
6.01
8.98
12.00
15.99
17.96
20.00
19.97
19.95
19.96
19.95
16.52
17.97
19.96
23.97
27.96
31.96
16.15
17.95
19.97
23.98
27.95
31.97
CLAFT
.0012
.0028
.0047
.0053
.0074
.0000
.0014
.0030
0048
0074
0102
0199
0251
0042
0054
.0073
.0094
.0120
.0148
.0257
.0310
.0275
.0306
0320
0331
O355
0198
0229
0273
0416
.0556
.0730
.0242
.0283
.0328
.0485
.0612
.0792
CDAFT
.0052
.0049
.0049
.0049
.0049
.0050
•0051
.0054
0059
0067
0079
0119
0148
0046
0048
.0053
.0061
.0071
.0087
.0134
.0166
.0173
0183
0189
0193
0203
0123
0141
.0173
.0277
.0409
.0600
.0132
.0158
.0192
.0308
.0440
.0644
CMAFT
-•0039
-.0060
-.0086
-.0095
-.0124
-.0030
-.0040
-.0050
-.0064
-.0088
-.0120
-.0214
-.0258
-.0088
-.0096
-.0109
-.0126
-.0153
-.0185
-.0291
-.0339
-.0292
-.0336
-.0358
-.0373
-.0409
-.0226
-.0251
-.0293
-.0453
-.0646
-.0936
-.0290
-.0324
-.0371
-.0550
-.0731
-.1037
CLN
.0055
.0073
.0129
.0145
.0189
.0060
.0083
.0091
.0117
.0142
.0165
.0221
.0253
.0152
.0161
.0176
.0196
.0219
.0244
.0313
0355
0270
0305
0328
0346
0378
0196
0218
.0247
.0286
.0332
.0337
.0264
.0313
.0346
.0390
.0428
.0439
CDN
.0004
-•0004
.0017
.0016
.0039
0003
0006
0013
0026
0042
0058
0102
.0132
.0018
.0027
.0034
.0047
.0062
.0087
0134
0162
0153
0151
0171
0180
.0216
.0096
.0115
.0144
.0211
.0282
.0365
.0112
.0145
.0173
.0242
.0324
.0422
CMN
-.0129
-.0149
-•0243
-.0271
-.0345
-•0132
-.0137
-•0135
-.0154
-.0173
-.0196
-•0233
-•0254
-•0269
-.0278
-.0286
-.0305
-.0326
-.0357
-.0417
-.0451
-•0265
-.0371
-.0425
-.0462
-.0547
-•0226
-•0241
-.0262
-.0299
-•0349
-.0407
-.0400
-.0435
-.0463
-.0518
-.0579
-.0675
41
Table 9. Concluded
(b) Concluded
MACH
150
151
151
151
150
152
150
151
150
151
151
150151
.150
• 150
.151
150
150
150149
149149
149
152
153
148
149
152
149150
147
148
151
.149
.149
.148
.151
.151
.151
.150
NPR ALPHA CLAFT CDAFT CMAFT CLN CDN CMN
1.00 .01 .0030 .0058 -.0064 .0351 .0008 -.0263
2.01 -.03 .0063 .0067 -.0111 .0363 .0078 -.0335
2.60 -.03 .0094 .0075 -.0150 .0322 .0221 -.0369
3.04 -.01 .0090 .0076 -.0146 .0249 .0188 -.0316
3.76 .00 .0118 .0084 -.0182 .0327 .0104 -.0434
1.00 -1.59 .0019 .0069 -.0068 .0018 -.0030 -.0119
1.00 -.01 .0029 .0066 -.0077 .0039 -.0045 -.0099
1.00 3.00 .0064 .0073 -.0109 .0031 -.0036 -.0087
1.00 6.00 .0050 .0071 -.0077 .0050 -.0048 -.0115
1.00 8.99 .0088 .0082 -.0117 .0177 .0123 -.0173
1.00 11.99 .0126 .0095 -.0160 .0193 .0158 -.0174
1.00 16.01 .0178 .0118 -.0211 .0277 .0221 -.0247
1.00 18.00 .0270 .0160 -.0314 .0301 .0256 -.0256
2.61 -1.96 .0062 .0075 -.0106 .0166 .0216 -.0328
2.62 -.03 .0084 .0076 -.0127 .0127 .0213 -.0306
2.62 3.00 .0067 .0080 -.0096 .0193 .0209 -.0350
2.61 5.99 .0095 .0088 -.0119 .0194 .0206 -.0353
2.61 8.99 .0114 .0097 -.0133 .0179 .0253 -.0369
2.62 12.00 .0152 .0113 -.0178 .0263 .0274 -.0406
2.61 15.98 .0222 .0147 -.0266 .0296 .0344 -.0476
2.61 17.86 .0311 .0190 -.0369 .0290 .0378 -.0458
1.00 20.02 .0247 .0167 -.0282 .0210 .0133 -.0201
2.01 19.99 .0274 .0190 -.0321 .0085 .0080 -.0173
2.63 19.97 .0275 .0200 -.0336 .0038 .0158 -.0226
3.01 19.96 .0276 .0202 -.0344 .0142 .0182 -.0336
3.80 19.96 .0310 .0229 -.0404 .0146 .0230 -.0413
1.00 15.98 .0173 .0126 -.0234 -.0008 .0071 -.0115
1.00 17.96 .0221 .0145 -.0285 .0069 .0082 -.0173
1.00 19.97 .0259 .0169 -.0315 .0138 .0135 -.0197
1.00 23.98 .0300 .0219 -.0335 .0329 .0233 -.0328
1.00 27.97 .0432 .0329 -.0502 .0391 .0315 -.0369
1.00 31.96 .0550 .0461 -.0678 .0495 .0461 -.0471
1.00 34.98 .0638 .0574 -.0829 .0487 .0512 -.0493
2.59 15.97 .0198 .0143 -.0248 .0169 .0301 -.0427
2.59 17.97 .0234 .0157 -.0286 .0190 .0317 -.0482
2.59 19.97 .0295 .0191 -.0353 .0165 .0317 -.0439
2.59 23.97 .0317 .0235 -.0358 .0231 .0335 -.0508
2.59 27.98 .0462 .0356 -.0537 .0284 .0366 -.0522
2.59 31.97 .0570 .0494 -.0707 .0350 .0450 -.0613
2.59 34.96 .0667 .0623 -.0877 .0322 .0478 -.0638
42
Table 10. Longitudinal Aerodynamic Characteristics for A/B Nozzle With 100/25
A/B Sidewalls and 6v,p = 0°
(a) Total aft end
MACH
1.201
1.198
1.198
1.200
1.200
1.203
1.199
1.200
1.201
1.201
1.198
1.200
1.198
1.201
1.201
1.200
1.200
1.200
1.201
1.196
1.199
.903
.902
.901
.898
.900
.899
.902
.901
.900
.902
.900
.899
.898
.899
.902
.901
.896
.901
.899
.899
.901
NPR ALPHA CLT C(D-F) CMT CL CD CM
.95
3.01
5. O0
6.98
9.01
.95
93
91
89
87
81
75
.70
7.00
7.00
7. O0
7.00
6.99
7.01
6.96
6.99
1.09
2.00
3.03
5.03
7.03
i. II
1.09
1.09
I.I0
I.i0
i. I0
1.09
1.08
4.99
5.01
5.00
4.98
5.01
4.99
4.99
5.00
-.01
.00
.01
.02
.01
-2.02
.00
3.02
6.00
9.02
12.01
15.99
18.01
-2.03
-.01
3.00
6.03
9.01
12.00
16.02
18.00
.00
-.02
-.01
.00
.02
-2.02
-.02
2.98
6.00
9.01
11.99
16.00
18.00
-2.04
-.032.98
6.02
9.00
12.01
16.03
17.99
-.0095
-.0086
-.0106
-.0110
-.0111
-.0221
-.0105
.0053
.0216
.0349
.0468
.0623
.0723
-.0262
-.0120
.0066
.0271
.0461
.0637
.0870
.0995
-.0O75
-.0070
-.0076
-.0075
-.0084
-.0070
- 0076
- 0043
- 0061
- 0034
0136
0284
.0364
-.0130
-.0095
-.0005
.0034
.0127
.0352
.0595
.0717
.0175
-.0147
-.0452
-.0762
-.1084
.0191
.0180
.0187
.0222
.0288
.0378
.0475
.0543
-.0752
-.0763
-.0759
-.0726
-.0663
-.0582
-.0469
-.0405
.0035
-.0258
-.0518
-.1062
-.1605
.0034
.0036
.0031
.0024
.0027
.0076
.0174
.0249
-.1051
-.1051
-.1056
-.1062
-.1045
-.0990
-.0867
-.0781
.0058
.0065
.0122
.0159
.0190
.0139
.0055
-.0062
-.0199
-.0310
-.0453
-.0618
-.0730
.0226
.0161
.0091
-.0020
-.0143
-.0286
-.0466
- 0571
0050
0075
0111
0165
0224
0034
.0050
.0057
.0076
.0074
-.0031
-.0146
-.0217
.0156
.0169
.0171
.0193
.0185
.0077
-.0067
-.0149
-.0095
-.0086
-.0106
-.0110
-.0112
-.0221
-.0105
0054
0216
0350
0469
0624
0724
-.0230
-.0120
.0019
.0175
.0320
.0449
.0620
0715
- 0075
- 0070
- 0076
- 0075
- 0085- 0071
-.0076
-.0043
-.0061
-.0034
.0136
.0285
.0365
-.0091
-.0095
-.0061
-.0079
-.0042
.0127
.0296
.0384
.0175
.0165
.0159
.0144
.0128
.O191
.0180
.0187
.0222
.0288
0378
0475
0543
0155
0145
0149
0178
0235
0308
0406
0460
0035
.0027
.0038
.0033
.0020
.0034
.0036
.0031
.0025
.0028
.0076
.0174
.0249
.0032
.0030
.0025
.0021
.0024
.0072
.0175
.0249
.0058
.0035
.0062
.0069
.0069
.0139
.0055
-.0062
-.0199
-.0310
-.0453
-.0618
- 0730
0136
0071
0000
- 0110
- 0233
-.0377
-.0557
-.0661
.0050
.0049
.0057
.0057
.0062
.0034
.0050
.0057
.0076
.0074
-.0031
-.0146
-.0217
.0049
.0063
.0064
.0085
.0078
-.0030
-.0174
-.0256
43
Table 10. Continued
MACH
600
603
598
597
60O
599
601
604
601
601
599
600
598
599
602
600
599
600
603
598
600
151
149
150
150
152
151
151
151
150
149
149
151
151
149
151
151
151
151
150
150
151
NPR
1.03
2.01
2.99
3.50
5. O0
1.03
1.03
1.03
1.03
1.03
1.03
1.03
1.02
3.48
3.54
3.50
3.50
3.50
3.51
3.49
3.50
1.00
1.99
2.61
3.00
3.79
1.03
1. O0
1.00
1.00
i .00
i.00
1.00
I. 00
2.61
2.61
2.61
2.61
2.61
2.61
2.61
2.61
ALPHA CLT
(a) Concluded
C(D-F) CMT CL CD CM
•00 -.0076 .0049 .0040 -.0076 .0049 .0040
•02 -.0058 -.0603 .0093 -.0058 .0040 .0034
•02 -.0058 -.1193 .0159 -.0059 .0051 .0039
•02 -.0055 -.1501 .0190 -.0055 .0051 .0038
•02 -.0051 -.2399 .0275 -.0052 .0044 .0035
-1.89 -.0069 .0043 .0037 -.0069 .0043 .0037
-.02 -.0042 .0041 .0031 -.0042 .0041 .0031
3.00 -.0015 .0042 .0029 -.0015 .0042 .0029
6.01 .0017 .0049 .0015 .0018 .0049 .0015
9.00 .0058 .0059 -.0013 .0059 .0059 -.0013
12.00 .0106 .0076 -.0059 .0106 .0076 -.0059
15.99 .0258 .0139 -.0181 .0259 .0140 -.0181
18.00 .0342 .0191 -.0239 .0343 .0191 -.0239
-1.83 -.0103 -.1486 .0191 -.0055 .0047 .0042
-.02 -.0037 -.1502 .0184 -.0036 .0045 .0033
2.98 .0071 -.1489 .0176 -.0008 .0045 .0026
6.03 .0180 -.1479 .0165 .0019 .0051 .0015
9.00 .0301 -.1455 .0130 .0062 .0059 -.0019
12.01 .0428 -.1413 .0078 .0111 .0078 -.0070
15.98 .0697 -.1339 -.0059 .0274 .0143 -.0209
18.01 .0836 -.1267 -.0127 .0363 .0193 -.0277
•00 -.0062 .0192 -.0015 -.0062 .0192 -.0015
•01 .0045 -1.0258 .0894 .0044 .0018 -.0042
•02 .0018 -1.5807 .1525 .0013 .0201 .0003
•02 .0026 -1.9654 .1917 .0021 .0145 .0011
•02 .0047 -2.6482 .2583 .0040 .0125 -.0019
-1.53 -.0002 -o0019 -.0008 -.0002 -.0019 -.0008
•03 .0271 .0085 -.0109 .0271 .0085 -.0109
2.99 .0289 .0086 -.0102 .0289 .0086 -.0102
5.99 .0326 .0103 -.0102 .0327 .0103 -.0102
8.98 .0344 .0150 -.0128 .0344 .0150 -.0128
11.99 .0404 .0217 -.0185 .0405 .0217 -.0185
15.99 .0534 .0286 -.0297 .0535 .0286 -.0297
18.00 .0585 .0366 -.0377 .0586 .0366 -.0377
-1.55 -.0264 -1.6118 .1534 .0178 .0167 -.0014
•02 .0181 -1.5804 .1493 .0176 .0164 -.0024
2.98 .0986 -1.5734 .1501 .0155 .0207 -.0016
5.99 .1803 -1.5564 .1495 .0151 .0190 -.0010
9.01 .2752 -1.5474 .1448 .0261 .0237 -.0064
11.99 .3625 -1.5447 .1431 .0289 .0267 -.0096
15.99 .4893 -1.5211 .1312 .0432 .0356 -.0227
17.99 .5489 -1.4790 .1178 .0547 .0437 -.0343
44
Table 10. Continued
MACH
1 201
1 198
1 198
1 200
1 200
1 203
1 199
1.200
1.201
1.201
1.198
1.200
1.198
1.201
1.201
1.200
1.200
1.200
1 201
1 196
1 199
903
902
901
.898
.900
.899
.902
.901
.900
.902
.900
.899
.898
.899
.902
.901
.896
.901
.899
.899
.901
(b) Afterbody and nozzle
NPR ALPHA CLAFT CDAFT CMAFT
.95
3.01
5.00
6.98
9.01
.95
.93
.91
.89
.87
.81
.75
.70
7.00
7.00
7.00
7.00
6.99
7.01
6 96
6 99
1 09
2 O0
3 03
5 03
7.03
I.Ii
1.09
1.09
i. I0
I.I0
I.i0
I. 09
1.08
4.99
5.01
5. O0
4.98
5.01
4.99
4.99
5.O0
-.0086
-.0084
-.0084
-.0084
-.0085
-.0169
-.0083
.0038
.0180
.0301
.0403
.0528
.0603
-.0169
-.0083
.0036
0181
0301
0406
0530
0605
- 0033
- 0034
- 0034
- 0035
-.0035
-.0019
-.0034
-.0052
-.0060
-.0049
-.0005
.0140
.0194
-.0021
-.0034
-.0052
-.0053
-.0045
-.0001
.0151
.0205
-.01
.00
.01
.02
.01
-2.02
.00
3.02
6.00
9.02
12.01
15.99
18.01
-2.03
-.01
3.00
6.03
9.01
12.00
16.02
18.00
.00
-.02
-.01
.00
.02
-2.02
-.02
2.98
6.00
9.01
11.99
16.00
18.00
-2.04
-.03
2.98
6.02
9.00
12.01
16.03
17.99
.0084
.0086
.0086
.0086
.0086
.0093
.0087
.0093
0116
0151
0198
0264
0308
0094
0088
0093
.0116
0153
0198
0267
0309
0058
0053
0054
.0053
.0051
.0058
.0059
.0058
.0055
.0057
.0071
.0140
.0186
.0053
.0054
.0052
.0050
.0051
.0067
.0141
.0187
.0083
.0080
.0080
.0080
.0080
.0149
.0079
-.0023
-.0159
-.0287
-.0416
-.0553
-.0637
0150
0077
- 0023
- 0161
- 0288
- 0418
- 0556
- 0642
.0028
.0030
.0030
.0031
.0032
.0012
.0030
.0056
.0067
.0072
.0053
-.0058
-.0100
.0014
.0030
.0056
.0062
.0069
.0045
-.0072
-.0116
CLN
-.0009
-.0002
-.0022
-.0026
-.0027
-.0052
-.0022
.0016
.0036
.0049
.0065
.0096
.0121
-.0061
-.0037
- 0018
- 0005
0018
0043
0090
0109
-.0042
-.0036
-.0042
-.0040
-.0050
-.0052
-.0042
.0010
.0000
.0015
.0141
.0144
.0171
-.0071
-.0061
-.0009
-.0026
.0003
.0128
.0145
.0179
CDN
.0091
.0079
.0073
0058
0041
0098
0093
0094
0107
0137
0181
0211
0235
0061
.0057
.0056
.0062
.0083
.0110
.0139
.0152
-.0023
-.0026
-.0016
-.0020
-.0031
-.0024
-.0023
-.0026
-.0030
-.0029
.0005
.0034
.0063
-.0021
-.0023
-.0027
-.0029
-.0027
.0005
.0034
.0062
CMN
-.0024
-.0045
-.0018
-.0011
-.0011
-.0010
-.0024
-.0039
-.0040
-.0023
-.0038
-.0066
-.0092
-.0013
-.0006
.0024
.0051
.0055
.0041
-.0001
-.0020
.0021
.0019
.0027
.0025
.0031
.0022
.0020
.0001
.0009
.0002
-.0084
-.0088
-.0117
.0035
.0033
.0008
.0023
.0009
-.0075
-.0102
-.0139
45
Table 10. Concluded
(b) Concluded
MACH NPR ALPHA CLAFT CDAFT CMAFT CLN CDN CMN
600 1.03 .00 -.0033 .0055
603 2.01 .02 -.0033 .0051
598 2.99 .02 -.0033 .0052
597 3.50 .02 -.0033 .0052
600 5.00 .02 -.0032 .0052
599 1.03 -1.89 -.0037 .0055
601 1.03 -.02 -.0031 .0054
604 1.03 3.00 -.0019 .0054
601 1.03 6.01 -.0005 .0056
601 1.03 9.00 .0019
599 1.03 12.00 .0047
600 1.03 15.99 .0147
598 1.02 18.00 .0194
599 3.48 -1.83 -.0037
602 3.54 -.02 -.0031
600 3.50 2.98 -.0018
599 3.50 6.03 -.0004
600 3.50 9.00 .0020
603 3.51 12.01 .0053
598 3.49 15.98 .0154
600 3.50 18.01 .0206
151 1.00 .00 -.0009
149 1.99 .01 -.0014
150 2.61 .02 -.0024
150 3.00 .02 -.0025
152 3.79 .02 -.0018
151 1.03 -1.53 -.0022
151 1.00 .03 - 0033
151 1.00 2.99 - 0017
150 1.00 5.99 - 0016
149 1.00 8.98 0003
149 1.00 11.99 0058
151 1.00 15.99 0143
.0029 -.0042 -.0006 .0011
.0030 -.0025 -.0011 .0005
.0029 -.0026 -.0001 .0011
.0029 -.0023 -.0001 .0009
.0029 -.0020 -.0007 .0006
.0028 -.0032 -.0012 .0009
•0028 -.0011 -.0012 .0003
.0024 .0005 -.0012 .0005
.0015 .0023 -.0007 .0000
.0061 -.0008 .0039 -.0002 -.0006
.0070 -.0038 .0059 .0006 -.0021
.0106 -.0134 .0112 .0033 -.0047
.0131 -.0172 .0149 .0059 -.0067
.0051 .0029 -.0018 -.0004 .0013
.0050 .0030 -.0005 -.0006 .0004
•0051 .0024 .0010 -.0006 .0002
•0052 .0015 .0023 -.0001 .0000
•0057 -.0007 .0042 .0003 -.0013
•0067 -.0045 .0058 .0010 -.0026
•0105 -.0143 .0119 .0038 -.0066
•0132 -.0187 .0157 .0061 -.0090
•0076 -.0019 -.0053
•0078 -.0012
•0076 .0002
•0075 .0007
•0079 .0003
0055 .0015
0051 0038
0050 0025
0047 0034
0052 0019
0066 - 0044
0098 - 0137
•0116 .0004
•0058 -.0059 -.0030
•0037 .0125 .0001
•0046 .0069 .0004
•0059 .0046 -.0022
0020 -.0074 -.0023
0304 .0034 -.0147
0306 .0036 -.0127
0343 .0056 -.0136
0341 .0099 -.0147
0347 .0151 -.0141
0392 .0188 -.0160
151 1.00 18.00
149 2.61 -I 55
151 2.61
.151 2 61 2
.151 2 61 5
.151 2 61 9
.150 2 61 11
.150 2 61 15
.151 2 61 17
02 -.0019
98 -.0008
99 -.0024
Ol .0007
99 .0046
99 .0115
99 .0157
0184 .0121 -
0022 .0065
0061
0065
0060
0068
0179
0023
0022
0018 .0164
0045 .0175
0011 .0254
0076 -.0033 .0244
0104 -.0104 .0317
0126 -.0144 .0390
0402 .0246 -.0199
0200 .0102 -.0036
0195 .0103 -.0046
0142 -.0034
0129 -.0055
0169 -.0075
0191 -.0062
0252 -.0123
0311 -.0199
46
Table 11. Lateral Aerodynamic Characteristics for A/B Nozzle With 100/25 A/B
Sidewalls and 5v,p = O°
MACH NPR ALPHA CROLLT CNT CYT CROLL CN CY
1.201
1.198
1.198
1.200
1.200
1.203
1.199
1.200
1.201
1.201
1.198
1.200
1.198
1.201
1.201
1.200
1.200
1.200
1.201
1.196
1.199
.903
.902
.901
.898
.900
.899
.902
.901
.900
.902
.900
.899
.898
.899
.902
901
896
901
899
899
901
.95 -.01
3.01 .00
5.00 .01
6.98 .02
9.01 .01
.95 -2.02
.93 .00
.91 3.02
.89 6.00
.87 9.02
.81 12.01
.75 15.99
.70 18.01
7.00 -2.03
7.00 -.01
7.00 3.00
7.00 6.03
6.99 9.01
7.01 12.00
6.96 16.02
6.99 18.00
1.09 .00
2.00 -.02
3.03 -.01
5.03 .00
7.03 .02
i. II -2.02
1.09 -.02
1.09 2.98
i. I0 6.00
i.i0 9.01
I.i0 11.99
1.09 16.00
1.08 18.00
4.99 -2.04
5.01 -.03
5.00 2.98
4.98 6.02
5.01 9.00
4.99 12.01
4.99 16.03
5.00 17.99
.0000
.0000
.0001
.0003
.0004
0000
0001
0001
0002
0002
0001
.0001
.0001
.0003
.0003
.0004
.0004
.0005
.0005
.0005
.0006
.0002
.0001
.0001
.0004
.0006
.0002
.0002
.0002
.0001
.0001
.0001
.0001
.0002
.0003
.0003
.0003
.0003
.0003
.0003
.0003
.0004
.0009
.0004
.0021
.0036
.0052
.0009
.0010
.0010
.0009
.0011
.0001
-.0004
-.0004
.0036
.0037
.0038
0038
0042
0037
0038
0038
0006
-.0012
-.0007
.0024
.0054
.0006
.0006
.0006
.0003
.0002
.0002
.0000
.0001
.0023
.0023
.0023
.0023
.0021
.0020
.0021
.0023
-.0012 .0000 .0009 -.0012
-.0009 .0000 .0007 -.0011
-.0032 .0001 .0007 -.0009
-.0054 .0003 .0006 -.0007
-.0076 .0004 .0005 -.0004
-.0012 .0000 .0009 -.0012
-.0014 .0001 .0010 -.0014
-.0020 .0001 .0010 -.0020
-.0024 .0002 .0009 -.0024
-.0024 .0002 .0011 -.0024
-.0020 .0001 .0001 -.0020
-.0012 .0001 -.0004 -.0012
-.0011 .0001 -.0004 -.0011
-.0054 .0003 .0005 -.0006
-.0056 .0003 .0007 -.0009
-.0060 .0004 .0008 -.0013
-.0063 .0004 .0007 -.0015
-.0068 .0005 .0011 -.0021
-.0075 .0005 .0007 -.0027
-.0076 .0005 .0008 -.0029
-.0076 .0006 .0007 -.0029
-.0024 .0002 .0006 -.0024
-.0002 .0001 .0000 -.0016
-.0010 .0001 -.0001 -.0013
-.0054 .0004 .0000 -.0013
-.0096 .0006 .0000 -.0012
-.0023 .0002 .0006 -.0023
-.0023 .0002 .0006 -.0023
-.0025 .0002 .0006 -.0025
-.0019 .0001 .0003 -.0019
-.0016 .0001 .0002 -.0016
-.0017 .0001 .0002 -.0017
-.0013 .0001 .0000 -.0013
-.0020 .0002 .0001 -.0020
-.0050 .0003 -.0001 -.0010
-.0050 .0003 -.0001 -.0010
-.0050 .0003 -.0001 -.0010
-.0052 .0003 -.0001 -.0012
-.0046 .0003 -.0003 -.0006
-.0044 .0003 -.0004 -.0004
-.0047 .0003 -.0003 -.0007
-.0055 .0004 -.0001 -.0015
47
Table 11, Concluded
MACH
.600
.603
.598
.597
•600
.599
.601
•604
•601
.601
.599
•600
.598
.599
602
600
599
600
603
598
600
151
149
150
150
152
.151
151
151
150
149
149
151
151
149
151
151
151
.151
.150
.150
.151
NPR
1.03
2.01
2.99
3.50
5.00
1.03
1.03
1.03
1.03
i .03
1.03
1.03
1.02
3.48
3.54
3.50
3.50
3.50
3.51
3.49
3.50
1.O0
1.99
2.61
3.O0
3.79
1.03
I. 00
1. O0
1.00
1.00
1.00
1.00
1.00
2.61
2.61
2.61
2.61
2.612.61
2.612.61
ALPHA
.00
.02
.02
.02
.02
-1.89
-.02
3.00
6.01
9.00
12.00
15.99
18.00
-1.83
-.02
2.98
6.03
9.00
12.01
15.98
18.01
.00
.01
.02
.02
.02
-1.53
.03
2.99
5.99
8.98
11.99
15.99
18.00
-1.55
.02
2.98
5.99
9.01
11.99
15.99
17.99
CROLLT CNT CYT
.0003
-.0001
.0000
.0002
.0007
.0003
.0003
.0003
.0003
.0003
.0003
.0002
.0002
.0001
.0002
.0002
.0002
.0002
.0002
.0003
.0003
.0026
-.0015
-.0012
-.0001
.0025
.0022
.0021
.0020
.0016
.0016
.0015
.0014
.0013
-.0018
-.0017
-.0017
-.0020
-.0020
-.0023
-.0022
-.0022
.0003
-.0028
-.0013
.0005
.0056
.0003
.0003
.0004
.0003
.0001
.0001
.0003
.0002
.0004
.0006
.0005
.0005
.0004
.0005
.0006
.0008
.0042
-.0420
-.0333
- 0162
0233
0039
0043
0038
0034
.0033
.0030
.0027
.0026
-.0353
-.0345
-.0344
-.0345
-.0352
-.0355
-.0357
-.0350
-.0020
.0019
-.0006
-.0032
-.0107
-.0020
-.0022
-.0023
-.0022
-.0018
-.0021
-.0026
-.0027
-.0033
-.0036
-•0036
-.0036
-.0033
-.0036
-.0041
-.0050
-.0225
.0294
.0142
-•0105
-.0649
-.0192
-.0211
-.0192
-.0161
-.0161
-.0143
-.0137
-.0121
.0214
.0210
.0209
.0226
.0244
.0263
.0250
.0246
CROLL
.0003
-.0001
.0000
.0002
.0007
.0003
.0003
.0003
.0003
.0003
.0003
.0002
.0002
.0001
.0002
.0002
.0002
.0002
.0002
.0003
.0003
.0026
-.0015
-.0012
-.0001
.0025
.0022
.0021
.0020
.0016
.0016
.0015
.0014
.0013
-.0018
-.0017
-.0017
-.0020
-.0020
-.0023
-.0022
-.0022
CN
.0003
-.0001
-.0001
.0000
.0001
.0003
.0003
.0004
.0003
.0001
.0001
.0003
.0002
.0001
.0001
.0001
.0001.0000
.0001
.0002
.0004
.0042
.0028
.0001
.0041
.0018
.0039
.0043
.0038
.0034
.0033
.0030
.0027
.0026
-.0012
-.0012
-.0012
-.0016
-.0021
-.0021
-•0019
-.0017
CY
-.0020
-.0012
-.0014
-.0016
-.0017
-.0020
-.0022
-.0023
-•0022
-.0018
-.0021
-.0026
-.0027
-.0018
-.0018
-.0020-.0020
-.0017
-.0020
-.0025
-.0034
-.0225
-.0217
-.0177
-•0245
-.0177
-.0192
-.0211
-.0192
-.0161
-.0161
-.0143
-.0137
-.0121
-.0112
-.0108
-.0107
-.0089
-.0072
-.0056
-.0072
-.0072
48
Table 12. Longitudinal Aerodynamic Characteristics for Dry Nozzle With 100/25
A/B Sidewalls and 6v,p = 0 °
(a) Total aft end
MACH
1.200
1 200
1 200
1 202
1 200
1 201
1 202
1 202
1 201
1 200
1.200
1.202
1.197
1.202
1.202
1.201
1.200
1.200
1.201
1.203
1.199
.899
.900
.897
.896
.902
.899
.900
.903
.901
.902
.901
.901
.900
.901
900
900
903
899
90O
902
898
NPR ALPHA CLT C(D-F) CMT CL CD CM
.93
2.96
5.01
7.06
8.96
.94
.92
88
84
80
77
76
76
7 03
7 06
7 O0
6 99
6.98
6.99
7.01
6.98
I.I0
2.01
2.99
4.97
7.01
I.ii
I.I0
I.I0
1.10
I.I0
I.I0
1.09
1.06
4.99
4.99
5.00
5.01
4.99
4.99
5. O0
4.99
Ol
Ol
02
Ol
02
-20l
Ol
30l
6 O0
90l
11.99
16.02
18.00
-2.01
.01
3.03
5.99
9.01
12.00
15.99
17.98
-.03
-.01
-.01
.00
.00
-2.03
.03
3.03
6.00
9.01
11.99
16.03
18.00
-2.02
.00
3.03
6.01
8.99
12.01
16.03
17.99
-.0075
-.0077
-.0087
-.0103
-.0102
-.0230
-.0078
0115
0311
0424
0570
0725
0810
- 0213
- 0088
0094
0292
0463
.0649
.0859
.0981
-.0085
-.0090
-.0081
-.0077
-.0076
-.0069
-.0067
-.0016
-.0023
.0045
.0200
.0375
.0423
-.0093
-.0072
.0013
.0033
.0107
.0322
.0553
.0659
.0167
-.0042
-.0246
-.0463
-.0672
.0184
.0171
.0195
.0250
.0317
.0401
0506
0571
- 0446
- 0457
- 0441
- 0408
-.0333
-.0255
-.0146
-.0073
.0039
-.0164
-.0338
-.0701
-.1071
.0040
.0040
.0038
.0036
.0047
.0099
.0215
.0277
-.0695
-.0699
-.0702
-.0701
-.0694
-.0634
-.0507
-.0432
005O
0064
0095
0137
0154
0185
0033
- 0142
- 0329
- 0408
- 0559
-.0704
-.0798
.0197
.0129
.0027
-.0095
-.0221
-.0378
-.0551
-.0662
.0045
.0082
.0091
.0123
.0158
.0033
.0038
.0036
.0035
-.0023
-.0119
-.0254
-.0257
.0102
.0120
.0120
.0143
.0123
.0010
-.0134
-.0206
- 0075
- 0077
- 0088
- 0104
- 0102
- 0230
- 0078
0115
0311
.0424
.0571
.0726
.0811
-.0191
-.0088
.0061
.0228
.0366
.0521
.0689
.0791
-.0085
-.0090
-.0081
-.0077
-.0076
-.0069
-.0067
-.0015
-.0022
.0046
.0201
.0376
.0424
-.0067
-.0072
-.0026
-.0044
-.0008
.0169
.0350
.0432
0167
0166
0171
0163
0150
0184
0171
0195
0250
.0317
.0401
.0506
.0571
.0177
.0169
.0179
.0209
.0279
.0352
.0450
.0517
.0039
.0031
.0038
.0040
.0033
.0040
.0040
.0038
.0036
.0047
.0100
.0215
.0278
0041
0038
0038
0032
0037
0088
0202
0273
.0050
.0044
.0056
.0080
.0078
.0185
.0033
-.0142
-.0329
-.0408
-.0559
-.0704
-.0798
.0140
.0071
-.0030
-.0153
-.0278
-.0435
-.0608
-.0720
0045
0062
0055
0054
0056
0033
0038
0036
.0035
-.0023
-.0119
-.0254
-.0257
.0034
.0051
.0051
.0074
.0054
-.0059
-.0203
-.0275
49
Table 12. Continued
MACH
600
601
601
599
597
603
599
600
599
600
599
600
599
599
601
600
599
601
601
603
596
•600
.600
.600
.599
.599
.600
.599
.599
.601
.599
.599
.602
.599
.599
.598
.598
.599
NPR
1.04
1.98
2.99
3.50
4.98
1.04
i .04
1.04
1.04
1.05
1.05
1.05
1 05
3 53
3 51
3 50
3 49
3 49
3 49
3 50
3 48
1 05
2 00
3 O0
3 51
5 03
1 05
I 05
I 05
1.03
1.01
.98
3.48
3.49
3.49
3.49
3.50
3.50
ALPHA
.00
.02
.01
.01
.00
-1.90
.00
2.99
6.00
8.99
12.00
15.99
18.02
-i 88
033 O0
6 O0
9 O0
12 O0
16 O0
18 01
20 02
20 Ol
20 O0
20 02
20 00
16 66
18 O0
19 99
23 98
27 98
31.99
16.82
17.98
19.99
23.98
27.97
31.99
CLT
-.0081
-.0085
-.0070
-.0069
-.0056
-.0016
0000
0017
0064
0092
0145
0297
0371
-.0060
-.0004
0072
0157
0252
0356
0584
0716
0395
0537
0703
0782
1005
.0262
.0311
.0373
.0540
.0722
.0863
0569
0650
0769
1016
1307
1547
(a) Continued
C(D-F) CMT
.0037 .0043
-.0410 .0109
-.0813 .0125
-.1019 .0145
-.1639 .0197
.0049 .0010
.0048 .0016
.0047 .0028
.0056 -.0008
.0065 -.0026
.0085 -.0067
.0148 -.0185
.0195 -.0234
-.1021 .0127
-.1003 .0119
-.I000 .0117
-.0994 .0105
-.0969 .0073
-.0943 .0026
-.0856 -.0109
-.0810 -.0175
.0221 -.0251
-.0212 -.0200
-.0581 -.0223
-.0777 -.0213
-.1365 -.0174
.0138 -.0181
.0166 -.0210
.0212 -.0247
.0360 -.0404
.0566 -.0633
.0803 -.0903
-.0862 -.0117
-.0841 -.0153
-.0778 -.0211
-.0605 -.0392
-.0350 -.0689
-.0055 -.1017
CL
-.0081
-.0085
-.0070
-.0069
-.0056
-.0016
.0000
.0017
.0064
.0093
.0146
.0298
.0372
-.0025
-.0005
0017
0048
0089
0140
0299
0391
0396
0389
0415
0423
0431
0263
0313
0374
0542
0724
0865
0271
0327
.0411
.0589
.0814
.0991
CD
.0037
.0015
.0027
.0035
.0035
.0049
.0048
.0047
.0056
0065
0085
0148
0196
0044
0046
0046
0049
0061
0078
0142
0195
0221
0197
0214
0214
0215
0138
0166
0212
0360
0566
0803
0128
0158
0209
0360
0582
0838
CM
.0043
.0067
.0045
.0046
.0041
.0010
.0016
.0028
-.0008
-.0026
-.0067
-.0185
-.0234
.0027
.0020
.0018
.0006
-.0025
-.0072
-.0207
-.0274
-.0251
-.0243
-.0304
-.0312
-.0331
-.0181
-.0210
-.0247
-.0404
-.0633
-.0903
-.0214
-.0252
-.0310
-.0492
-.0788
-.1116
5O
Table 12. Continued
MACH
152
150
150
151
151
149
151
151
149
150
151
150
150
151
151
153
152
152
152
151
.151
.153
.150
.149
.150
.150
• 150
.150
.150
.151
.151
.151
.153
.152
149
149
149
152
150
153
152
NPR
1.00
2.02
2.61
2.98
3.86
1.00
1.00
I. 00
i. O0
1.00
1.00
1.00
i. O0
2.60
2.60
2.60
2.60
2.60
2.60
2.60
2.60
I.O0
1.98
2.59
3.03
3.81
2.79
1.01
i.O0
i.O0
i.O0
i.O0
1.00
1.00
2.63
2.60
2.60
2.60
2.60
2.61
2.61
ALPHA
02
02
Ol
01
O0
-I 32
.03
3.03
6.03
8.99
11.99
16.02
18.00
-1.36
.03
3.02
6.04
9.00
11.99
15.99
18.02
20.00
20.00
19.98
19.98
19.99
15.99
15.99
17.98
19.98
23.98
27.99
31.99
35.10
15.98
17.98
19.98
23.99
27.98
31.98
34.97
CLT
•0205
.0184
.0310
.0324
.0334
.0382
.0401
.0375
.0416
.0485
.0507
.0571
.0691
-•0003
.0257
.0827
.1356
.1988
.2540
.3450
.3886
.0483
.2804
.4387
5402
7148
3534
0098
0199
0368
0539
.0754
.0924
.0998
.3603
4079
4470
5147
6086
6688
7293
(a) Concluded
C(D-F) CMT CL CD CM
.0253 -.0121
-•7185 .0717
-1.0952 .0915
-1.3186 .1125
-1.8846 .1652
.0233 -.0154
.0173 -.0144
.0197 -.0107
.0187 -.0127
.0253 -.0162
.0274 -•0191
.0378 -.0281
.0448 -•0392
-1.0686 .0967
-1•0706 .0980
-1.0521 .0959
-1•0494 .0977
-I•0405 .0929
-1•0321 .0916
-1.0177 .0774
-1.0041 .0693
.0210 -.0273
-•6343 .0596
-1•0083 .0614
-1.2708 .0849
-1.7498 .1327
-1.1673 0964
0106 - 0092
0121 - 0172
0200 - 0261
0339 - 0371
0563 - 0583
0793 - 0798
0980 - 0943
-I 0684 0755
-i 0316 0619
-1.0189 0600
-.9411 0474
-.9178 0329
-.8252 0055
-.7816 -.0144
.0205
.0181
.0307
.0322
.0332
.0382
.0401
.0375
.0416
.0485
.0508
.0572
.0692
.0250
.0251
.0274
.0245
.0334
.0339
.0501
.0561
.0484
.0486
.0651
.0698
.0704
.0199
.0099
.0200
.0369
.0540
.0756
.0926
.I000
.0508
.0675
.0684
.0804
.0940
.1102
.1203
.0253
-.0065
.0002
.0056
.0098
.0233
.0173
.0197
.0187
.0253
.0274
.0378
.0448
-.0012
-.0028
-•0019
.0014
.0034
.0042
.0118
.0181
.0210
.0029
.0192
.0234
.0227
-.0029
.0106
.0122
.0200
.0339
.0564
.0794
.0981
.0122
0175
0225
0352
0511
0698
0895
-.0121
.0015
-.0137
-.0134
-.0128
-.0154
-.0144
-.0107
-.0127
-.0162
-.0191
-.0281
-.0392
-.0058
-.0045
-.0051
-.0038
-•0086
-•0102
-.0254
-.0339
-.0273
-.0074
-.0436
-•0459
-.0446
-.0193
-.0092
-.0172
-.0261
-.0371
-.0583
-.0798
-.0943
-.0324
-.0440
-.0464
-.0552
-.0724
-.0958
-.1165
51
Table 12. Continued
MACH
1.200
1.200
1.200
1.202
1.200
1.201
1.202
1.202
1.201
1.200
1.200
1.202
1.197
1.202
1.202
1.201
1.200
1.200
1.201
1.203
1.199
.899
.900
.897
.896
.902
.899
.900
.903
.901
.902
.901
.901
.900
.901
.900
.900
.903
.899
.900
.902
.898
(b) Afterbody and nozzle
NPR ALPHA CLAFT CDAFT CMAFT
.01
.01
.02
.01
.02
-2.01
.01
3.01
6.00
9.01
11.99
16.02
18.00
-2.01
.01
3.03
5.99
9.01
12.00
15.99
17.98
-.03
-.01
-.01
00
O0
-2 03
O3
3 03
6 O0
9 O1
11.99
16.03
18.00
-2.02
.00
3.03
6.01
8.99
12.01
16.03
17.99
.93
2.96
5.01
7.06
8.96
.94
.92
.88
.84
.80
.77
.76
.76
7.03
7.06
7. O0
6.99
6.98
6.99
7.01
6.98
i. I0
2.01
2.99
4.97
7.01
I.Ii
l.lO
I.I0
I.I0
I.i0
I.I0
1.09
1.06
4.99
4.99
5.00
5.01
4.99
4.99
5.00
4.99
- 0083
- 0081
- 0081
- 0082
- 0082
- 0166
- 0077
0052
0197
0304
0421
0547
0618
- 0166
- 0078
0045
0192
0303
0421
O545
0620
- 0031
- 0035
- 0035
- 0034
- 0033
- 0017
- 0031
- 0050
- 0052
- 0030
0010
0159
.0199
-.0017
-.0033
-.0048
-.0061
-.0036
.0006
.0158
.0211
.0084
.0084
•0085
.0085
.0086
.0091
.0086
.0092
.0116
.0154
.0201
.0268
.0313
.0092
.0086
.0092
.0116
.0154
.0201
.0267
.0313
.0060
.0057
.0057
.0057
.0056
.0058
.0059
.0059
.0056
.0059
.0075
.0150
.0191
.0056
0057
0056
0052
0055
0072
0149
0190
.0080
.0078
.0078
.0078
.0078
0149
0074
- 0037
- 0174
- 0299
- 0436
- 0574
-.0660
.0148
.0074
-.0032
-.O171
-.0299
-.0436
-.0574
-.0664
.0024
.0029
.0030
.0029
.0028
00110024
0052
0053
0047
0033
- 0076
- 0102
0010
0028
0052
0067
0059
0038
- 0072
- 0122
CLN
0OO8
0004
- 0006
- 0021
- 0020
- 0064
0000
0063
0114
0120
0150
0179
0193
- 0026
- 0010
.0017
.0036
0063
0100
0145
0171
- 0054
- 0055
-.0046
-.0043
-.0043
-.0052
-.0036
.0034
.0029
.0076
.0191
.0217
.0225
-.0050
-.0038
.0022
.0017
.0029
.0163
.0192
.0221
CDN
.0083
.0082
.0086
.0078
.0064
.0093
.0086
.0103
.0134
.0163
.0200
.0238
.0258
.0085
.0083
.0086
.0093
.0125
.0150
.0183
.0204
-.0021
-.0026
-.0019
-.0018
-.0023
-.0019
-.0019
-.0020
-.0020
-.0012
.0024
.0065
.0087
- 0015
- 0018
- 0018
- 0020
- 0019
0017
0054
0083
CMN
-.0030
-.0035
-.0022
.0001
.0000
.0036
-.0041
-.0105
-.0155
-.0109
-.0124
-.0129
-.0138
-.0008
-.0003.0002
.0018
.0021
.0001
-.0034
-.0056
.0021
.0033
.0025
.0025
.0028
.0023
.0014
-.0015
-.0018
-.0070
-.0151
-.0179
-.0155
.0024
.0023
-.0001
.0007
-.0005
-.0097
-.O131
-.0153
52
Table 12. Continued
(b) Continued
MACH NPR ALPHA CLAFT CDAFT CMAFT CLN CDN CMN
.600
.601
.601
.599
•597
.603
.599
600
599
600
599
600
599
599
601
600
599
.601
.601
.603
.596
.600
•600
.600
599
599
600
599
599
601
599
599
602
599
.599
.598
.598
.599
1.04 .00 -.0028 .0055 •0024 -.0053
1.98 .02 -.0031 •0053 .0030 -•0054
2.99 .O1 -.0032 .0054 .0031 -.0038
3.50 .01 -.0031 .0054 .0029 -.0038
4.98 .00 -.0032 .0053 .0030 -.0024
1.04 -1.90 -.0033 .0054 .0023 .0016
1.04 .00 -.0026 .0054 .0024 .0027
1.04 2.99 -.0019 .0053 .0027 .0037
1.04 6.00 .0002 .0056 .0008 .0062
1.05 8.99 .0023 .0061 -•0011 .0070
1.05 12.00 .0049 .0070 -.0038 .0097
1.05 15.99 .0148 .0108 -•0134 .0149
1.05 18.02 .0197 .0134 -.0175 .0175
3.53 -1.88 -.0036 .0053 .0027 .0011
3.51 .03 -.0027 .0052 .0023 .0022
3.50 3.00 -.0016 .0053 .0022 .0034
3.49 6.00 .0000 .0055 .0010 .0047
3.49 9.00 .0022 .0059 -.0010 .0067
3.49 12.00 .0052 .0069 -.0043 .0087
3.50 16.00 .0154 .0108 -.0141 .0145
3.48 18.01 .0204 .0135 -.0185 .0187
1.05 20.02 .0213 .0163 -•0204 .0184
2.00 20.01 .0216 .0162 -.0207 .0174
3.00 20.00 .0220 .0164 -.0216 .0194
3.51 20.02 .0224 .0166 -.0220 .0199
5.03 20.00 .0229 .0168 -•0228 .0202
1.05 16.66 .0144 .0119 -.0146 .0120
1.05 18.00 .0169 .0134 -.0166 .0143
1.05 19.99 .0213 .0163 -.0206 .0161
1.03 23.98 .0345 .0259 -.0351 .0196
1.01 27.98 .0495 .0393 -.0556 .0229
.98 31.99 .0642 .0563 -.0805 .0223
3.48 16.82 .0154 .0121 -.0159 .0118
3.49 17.98 .0177 .0135 -.0177 .0151
3.49 19.99 .0224 .0166 -.0221 .0187
3.49 23.98 .0363 .0265 -.0377 .0226
3.50 27.97 .0520 .0406 -.0595 .0294
3.50 31.99 .0677 .0586 -.0861 .0314
-.0019
-.0038
-.0026
-.0019
-.0018
-.0005
-.0006
-.0007
.0000
.0004
.0016
.0041
.0062
-.0009
-.0006
-.0007
-.0005
.0001
.0009
.0034
.0060
.0058
.0035
.0050
.0048
.0047
.0019
.0032
.0049
.0102
0173
0240
0007
0023
0043
0094
.O176
.0252
.0019
.0037
.0014
.0017
.0011
-.0014
-.0008
.0001
-.0015
-.0016
-.0029
-.0051
-.0060
.0000
-.0003
-.0003
-.0004
-.0015
-.0030
-•0066
-.0090
-.0048
-•0036
-.0088
-.0092
-.0102
-.0035
-.0044
-•0041
-.0052
-.0077
-.0099
-.0056
-.0075
-.0090
-.0115
-.0194
-.0254
53
Table 12. Concluded
MACH
152
150
150
151
151
149
151
151
149
150
151
150
150
151
151
153
152
152
152
151
151
153
150
149
150
150
150
150
150
151
151
151
153
152
149
149
149
152
150
153
152
(b) Concluded
NPR ALPHA CLAFT CDAFT CMAFT
.02
.02
.01
.01
.00
-1.32
.03
3.03
6.03
8.99
11.99
16.02
18.00
-1.36
.03
3.02
6.04
9.00
11.99
15.99
18.02
20.00
20.00
19.98
19.98
19.99
15.99
15.99
17.98
19.98
23.98
27.99
31.99
35.10
15.98
17.98
19.98
23.99
27.98
31.98
34.97
.0012
.0022
.0044
.0033
.0039
-.0031
-.0010
-.0011
.0004
.0029
.0079
.0161
.0224
.0036
.0036
.0059
.0086
.0124
.0128
.0200
.0281
.0198
.0175
.0201
.0198
.0200
.0085
.0082
.0172
.0189
.0267
.0383
.0512
.0560
.0097
.0165
.0191
.0266
.0378
.0500
.0606
I.O0
2.02
2.61
2.98
3.86
1.00
1.00
1.00
1.00
1.00
1.00
1.00
1.00
2.60
2.60
2.60
2.60
2.60
2.60
2.60
2.60
1.00
1.98
2.59
3.03
3.81
2.79
1.01
1.00
1.00
I.O0
1.00
1.00
I.O0
2.63
2.60
2.60
2.60
2.60
2.61
2.61
.0068 -.0043
.0073 -.0056
.0075 -.0082
.0076 -.0066
.0079 -.0063
.0058 .0030
.0053 .0011
.0052 .0026
.0054 .0023
.0059 .0002
.0070 -.0060
.0106 -.0148
.0136 -.0218
.0056 -.0052
.0058 -.0049
.0062 -.0068
.0068 -.0091
.0083 -.0133
.0091 -.0138
.0122 -.0219
.0163 -.0318
.0149 -.0203
.0150 -.0176
.0163 -.0214
.0162 -.0219
.0166 -.0234
.0113 -.0111
.0095 -.0097
.0124 -.0199
.0140 -.0204
.0199 -.0278
.0304 -.0424
.0439 -.0608
.0527 -.0703
.0104 -.0107
.0129 -.0187
.0147 -.0214
.0209 -.0266
.0311 -.0408
.0448 -.0595
.0577 -.0770
CLN
.0193
.0159
.0263
0288
0294
0413
0410
0386
0412
0457
.0429
0411
0468
0214
0215
0214
0159
.0210
.0210
.0300
.0280
.0286
.0311
.0450
.0500
.0504
.0114
.0017
.0028
.0180
.0273
.0373
.0414
.0440
.0411
.0510
.0494
.0539
.0562
.0602
.0597
CDN
.0185
-.0139
-.0073
-.0020
.0019
0175
0120
0145
0133
0194
0204
.0272
.0312
-.0068
-.0085
-.0081
-.0054
-.0049
-.0049
-.0004
.0018
.0061
-.0121
.0029
.0072
.0060
-.0142
.0012
-.0003
.0060
.0141
.0260
.0355
.0454
.0018
.0046
.0078
.0143
.0200
.0250
.0318
CMN
-.0078
.0071
-.0054
-.0069
-.0064
-.0185
-.0155
-.0133
-.0150
-.0164
-.0132
-.0133
-.0174
-.0006
.0004
.0017
.0053
.0047
.0037
-.0036
-.0021
-.0070
.0101
-.0222
-.0240
-.0211
-.0083
.0005
.0028
-.0057
-.0092
-.0158
-.0190
-.0241
-.0217
-.0253
-.0250
-.0286
-.0317
-.0363
-.0395
54
Table 13. Lateral Aerodynamic Characteristics for Dry Nozzle With 100/25 A/B
Sidewalls and 5v,p = 0°
MACH NPR ALPHA CROLLT CNT CYT CROLL CN CY
1.200 .93 .01 .0000 .0006 -.0007 .0000 .0006 -.0007
1.200 2.96 .01 .0000 .0005 -.0009 .0000 .0005 -.0008
1.200 5.01 .02 .0002 .0019 -.0031 .0002 .0007 -.0012
1.202 7.06 .01 .0003 .0030 -.0047 .0003 .0006 -.0012
1.200 8.96 .02 .0004 .0041 -.0061 .0004 .0006 -.0009
1.201 .94 -2.01 .0000 .0005 -.0009 .0000 .0005 -.0009
1.202 .92 .01 .0001 .0006 -.0011 .0001 .0006 -.0011
1.202 .88 3.01 .0002 .0006 -.0013 .0002 .0006 -.0013
1.201 .84 6.00 .0001 .0003 -.0007 .0001 .0003 -.0007
1.200 .80 9.01 .0002 .0001 -.0007 .0002 .0001 -.0007
1.200 .77 11.99 .0001 -.0002 -.0006 .0001 -.0002 -.0006
1.202 .76 16.02 .0001 -.0001 -.0004 .0001 -.0001 -.0004
1.197 .76 18.00 .0001 -.0004 .0004 .0001 -.0004 .0004
1.202 7.03 -2.01 .0003 .0030 -.0047 .0003 .0006 -.0011
1.202 7.06 .01 .0004 .0032 -.0051 .0004 .0008 -.0015
1.201 7.00 3.03 .0004 .0032 -.0052 .0004 .0009 -.0017
1.200 6.99 5.99 .0004 .0033 -.0053 .0004 .0009 -.0018
1.200 6.98 9.01 .0005 .0033 -.0056 .0005 .0009 -.0021
1.201 6.99 12.00 .0004 .0030 -.0055 .0004 .0006 -.0020
1.203 7.01 15.99 .0005 .0029 -.0050 .0005 .0006 -.0015
1.199 6.98 17.98 .0005 .0027 -.0046 .0005 .0003 -.0011
.899 I.i0 -.03 .0002 .0008 -.0021 .0002 .0008 -.0021
.900 2.01 -.01 .0001 -.0003 -.0008 .0001 .0005 -.0018
.897 2.99 -.01 .0002 .0000 -.0014 .0002 .0000 -.0012
.896 4.97 .00 .0004 .0023 -.0048 .0004 .0003 -.0016
.902 7.01 .00 .0006 .0045 -.0078 .0006 .0003 -.0015
.899 i. Ii -2.03 .0002 .0007 -.0021 .0002 .0007 -.0021
.900 1.10 .03 .0002 .0008 -.0023 .0002 .0008 -.0023
.903 I.I0 3.03 .0002 .0008 -.0023 .0002 .0008 -.0023
•901 I.i0 6.00 .0002 .0005 -.0020 .0002 .0005 -.0020
•902 I.i0 9.01 .0002 .0005 -.0017 .0002 .0005 -.0017
•901 i. I0 11.99 .0002 .0006 -.0019 .0002 .0006 -.0019
•901 1.09 16.03 .0002 .0003 -.0015 .0002 .0003 -.0015
•900 1.06 18.00 .0002 .0001 -.0014 .0002 .0001 -.0014
.901 4.99 -2.02 .0004 .0023 -.0048 .0004 .0002 -.0016
•900 4.99 .00 .0004 .0024 -.0050 .0004 .0003 -.0018
•900 5.00 3.03 .0004 .0024 -.0049 .0004 .0002 -.0017
.903 5.01 6.01 .0004 .0024 -.0052 .0004 .0003 -.0020
•899 4.99 8.99 .0004 .0021 -.0045 .0004 .0000 -.0012
•900 4.99 12.01 .0004 .0021 -.0045 .0004 .0000 -.0012
.902 5.00 16.03 .0004 .0022 -.0047 .0004 .0001 -.0015
.898 4.99 17.99 .0004 .0023 -.0048 .0004 .0002 -.0016
55
Table 13. Continued
MACH
•6OO
.601
•601
.599
•597
•603
.599
.600
•599
.600
.599
.600
.599
.599
.601
•600
.599
.601
• 601
.603
.596
.600
•600
60O
599
599
6O0
599
599
.601
.599
.599
•602
.599
.599
• 598
•598
.599
NPR
1.04
1.98
2.99
3.50
4.98
1.04
1.04
I.04
1.04
I. 05
1.05
1.05
I.05
3.53
3.51
3.50
3.49
3.49
3.49
3.50
3.48
1.05
2.00
3.00
3.51
5.03
1.05
1.05
1.05
1.03
1.01
.98
3.48
3.49
3.49
3.49
3.50
3.50
ALPHA
.00
.02
.01
.01
.00
-1.90
.00
2•99
6•00
8.99
12•00
15.99
18•02
-1.88
.03
3.00
6.00
9.00
12.00
16.00
18.01
20.02
20.01
20.00
20.02
20.00
16.66
18.00
19.99
23.98
27.98
31.99
16.82
17.98
19.99
23.98
27.97
31.99
CROLLT CNT CYT
.0001
-.0001
.0001
.0O02
.0005
•0003
.0003
•0003
.0003
.0003
.0003
.0003
.0003
.0003
.0004
.0003
.0003
.0003
.0003
.0004
.0004
.0000
-.0002
.0000
.0002
.0005
.0000
.0000
.0001
.0010
.0016
.0014
.0001
.0001
.0002
.0012
.0019
.0017
.0004
-.0019
-.0002
.0011
.0048
.0009
.0009
.0009
.0008
.0008
.0010
.0006
.0007
.0015
.0015
.0014
.0014
.0013
.0014
.0015
.0016
.0008
-.0012
.0004
.0016
.0052
.0003
.0004
•0009
.0073
.0126
.0124
.0010
.0012
.0017
.0087
.0141
.0144
-.0008
.0024
-.0005
-.0024
-.0076
-.0028
-.0026
-.0027
-.0026
-.0026
-.0031
-.0022
-.O025
-.0044
-.0042
-.0041
-.0039
-.0036
-.0042
-.0043
-.0046
-.0022
-•0002
-•0025
-.0043
-.0093
-.0010
-.0013
-•0026
-.0174
-.0272
-•0258
-.0024
-.0032
-.0044
-.0205
-•0303
-.0299
CROLL
.0001
-.0001
.0001
.0002
.0005
.0003
.0003
.0003
.0003
.0003
.0003
.0003
.0003
.0003
.0004
.0003
.0003
.0003
.0003
.0004
.0004
.0000
-.0002
.0000
.0002
.0005
.0000
.0000
.0001
.0010
.0016
.0014
.0001
.0001
.OO02
.0012
.0019
.0017
CN
.0004
.0001
-.0002
-.0001
.0000
.0009
.0009
.0009
.0008
.0008
.0010
.0006
.0007
.0003
.0003
.0003
.0002
.0001
.0003
.0003
.0004
.0008
.0007
.0004
.0004
.0004
.0003
.0004
.0009
.0073
.0126
.0124
-.OO02
.0000
.0005
.0075
.0129
.0132
CY
-.0008
.0000
.0000
-.0003
-.0003
-.0028
-.0026
-.0027
-.0026
-.0026
-.0031
-.0022
-.0025
-.0021
-.0020
-.0019
-.0018
-.0015
-.0020
-.0021
-.0025
-.0022
-.0025
-.0020
-.0021
-.0019
-.0010
-.0013
-.0026
-.0174
-.0272
-.0258
-.0004
-.0010
-.0023
-.0184
-.0281
-.0278
56
Table 13. Concluded
MACH
.152
•150
150
151
151
149
151
151
149
150
151
150
•150
.151
.151
.153
.152
.152
152
151
151
153
150
149
150
150
150
150
•150
.151
.151
.151
153
152
149
149
149
152
150
153
.152
NPR
1.00
2.02
2.61
2.98
3.86
I. O0
1.00
I.O0
1.00
1.00
i.O0
I.O0
1.00
2.60
2.60
2.60
2.60
2.60
2.60
2.60
2.60
i. O0
1.98
2.59
3.03
3.81
2.79
1.01
1.00
1.00
1.00
1.00
i.O0
1.00
2.63
2.60
2.60
2.60
2.60
2,61
2.61
ALPHA
.O2
.02
.01
.01
.00
-1.32
.03
3.03
6.03
8.99
11.99
16.02
18.00
-1.36
.03
3.02
6.04
9.00
11.99
15.99
18.02
20.00
20.00
19.98
19.98
19.99
15.99
15.99
17.98
19.98
23.98
27.99
31.99
35.10
15.98
17.98
19.98
23.99
27.98
31.98
34.97
CROLLT CNT CYT
.0045
.0009
.0023
•0030
.0056
.0028
.0026
.0026
.0024
.0024
0020
0023
0018
0002
0000
- 0003
- 0004
- 0006
-.0004
-.0003
-.0008
-.0008
-.0036
-.0020
-.0006
0009
0009
0017
0018
0017
0015
.0022
.0010
.0014
.0008
.0005
.0005
.0007
.0007
.0000
-.0003
CROLL CN CY
.0073 -.0305 .0045 .0073 -.0305
-.0266 .0105 .0009 .0043 -.0265
-.0096 -.0157 .0023 .0051 -.0301
.0031 -.0301 .0030 .0037 -.0241
.0371 -.0793 .0056 .0047 -.0257
•0045 -.0188 .0028 .0045 -.0188
•0047 -.0200 .0026 .0047 -.0200
.0042 -.0167 .0026 .0042 -.0167
•0043 -.0170 .0024 .0043 -.0170
•0042 -.0168 .0024 .0042 -.0168
•0036 -.0132 .0020 .0036 -.0132
•0034 -.0147 .0023 .0034 -.0147
•0030 -.0113 .0018 .0030 -.0113
-.0143 .0012 .0002 .0006 -.0135
-.0144 .0013 .0000 .0005 -.0134
-.0144 .0030 -.0003 .0002 -.0114
-.0146 .0046 -.0004 .0000 -.0099
-.0150 .0063 -.0006 -.0004 -.0081
-.0152 .0064 -.0004 -.0006 -.0081
-.0149 .0048 -.0003 -.0002 -.0097
-.0150 .0051 -.0008 -.0001 -.0095
.0001 .0002 -.0008 .0001 .0002
-.0331 .0349 -.0036 -.0011 -.0036
-.0169 .0110 -.0020 -.0014 -.0045
-.0013 -.0100 -•0006 -.0025 -.0014
.0273 -.0486 .0009 -•0035 .0028
-.0107 .0035 .0009 -.0028 -.0011
.0007 -.0026 .0017 .0007 -.0026
.0012 -.0043 .0018 .0012 -.0043
.0007 -.0025 .0017 .0007 -.0025
.0006 -.0023 .0015 .0006 -.0023
.0019 -.0046 .0022 .0019 -.0046
-.0029 .0073 .0010 -.0029 .0073
-.0029 .0059 .0014 -.0029 .0059
-.0152 .0059 .0008 -.0009 -.0078
-.0163 .0082 .0005 -.0011 -.0069
-.0161 .0081 .0005 -.0008 -.0070
-.0154 .0048 .0007 -.0007 -.0097
-.0145 .0044 .0007 .0006 -.0105
-.0186 .0159 .0000 -.0043 .0019
-.0208 .0217 -.0003 -.0064 .0075
57
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L-84-12,085
Figure 2. Model with afterburner power nozzles installed in the Langley 16-Foot Transonic Tunnel.
59
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FS 66.30 FS 70.48
4.18
'(--1.24 -_i < 2 II
.TO--,'-
FS 61.51 I
• _ • la
3.65 2 1.i9
Sedion A-A
Afterburner Dower, 6 -0 °v,p
FS 66.30 FS 70.45
4.15 l.
2.14 --_--J,'-1:1-12,-0
15°
.20 R--,., -•,,_-- 1.25 -_-_
,t 3.30
Section A-A
Afterburner power, 6 • 15°v,p
T1.59
I nstrumentation section
VIi
i3,65
FS 66.30 FS 70.39
, ,, _"--i. 05 "_- -- 2.18 --
\\
L,: $
_-_ _. t_'_dy/______
=LLV__ .8g • !
210 .20R _ _,_'20R'I_ I
Section A-A
Dry power, 6v, p-O°
l
1.02
Total-temperature
3.00
i
i i L
J
J- i ,, /
probe
/
///,
Total-pressure rake _ Left rear view
Ilooking upstream)
_A 4"13 _.33
_- Splitter plate
(a) Nozzles.
Figure 5. Nozzle geometric characteristics. All linear dimensions in inches.
62
FS 66.30 6 "0 °v,p
FS 67.57 A/B sidewall
Percent sidewall 25 50 100
FS 68.85 FS 70.48
FS 69.40
Dry power nozzle
A/B sidewall
Percent sidewall 25 100i I
FS 68.85 FS 70.39
FS 66.30
Afterburner power nozzles
6 - 15°v,p
A/B sidewall
6 -0 °v,p
Dry power sidewall
FS 66.30
Sidewall geometry
FS 67.57
I
Percent sidewall 25 50 100
Top view
(b) Sidewall configurations.
Figure 5. Continued.
• • _ • ' . r "P
63
(c) Afterburnerpowernozzlewith 100-percentsidewallsand5v,p= 0°.
Figure5. Concluded.
L-84-12,084
ORIGINAL PAGE
COLOR PHOTOGRAPH
64
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oo
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65
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0 _ 0_0 ---0---0
ii •
h_
-- Outboard row, y/-_ = -0.838f..,.
(bottom flap only)
h.
-- Centerline row, y/-_ = 0
(top and bottom flap)
Inboard row, y/-_ = 0.838
(bottomflap only)
Xr
/."2 17 "_
x//.
O.36
.121.091.451.81
O.167
•334
•501
•667
•835
(b) Internal nozzle.
Figure 6. Concluded.
66
1.00
Percent sidewall
Left . Right0 100 100[] 50 5O0 25 25
I. 00
• 96
F .92F.
I
• 88
.84
• 96
FG.92
F.I
• 88
.84
(
1.00 2O
W__.P__W.
I
.96
• 92
•88
8p, dog
I0
-I00 2 4 6 0 2 4
NPR NPR
Figure 7. Effect of cutback sidewalls on A/B nozzle static performance with c_ = 0° and 6v,p = 0°.
67
F
F.I
I. O0
•96
• 92
• 88
.84
r
Percent sidewall
Left Right© 100 100[] 50 50
<> 25 25
FG
F.I
1.00
.96
.92
• 88
.84
1.00 3O
W__E
W.I
• 96
• 92
•88
6p, deg
20
10
0 2 4 6 0 2 4
NPR NPR
Figure 8. Effect of cutback sidewalls on A/B nozzle static performance with c_ = 0 ° and/_v,p = 15%
68
N
m
0
8
000
0
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z
0
m
0
0 8
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70
Percent sidewall
Left RightO 100 100
1.2 O 25 25 .4
.8
Cm, t
-.4
.8
-.zl CD-F -1.2
.4 -1.6
-.8
,7 -2.0
-2.4
-2.8
-1.2 -3.20 1 2 3 4 0 1 2 3
NPR NPR
(a) M = 0.15.
Figure 10. Effect of cutback sidewalls on total lift coefficient, drag coefficient, and pitching-moment coefficient
(including thrust) with _ = 0 ° and 5v,p = 0 °.
71
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Percent sidewall
Left Right© i00 i00
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-.4
-.8
-1.2
CD-F
-1.6
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-2.4
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4 -3.20 2
NPR
(a) M = 0.15.
Figure 11. Effect of cutback sidewalls on total lift coefficient, drag coefficient, and pitching-moment coefficient
(including thrust) with a = 0° and 6v,p = 15 °.
75
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'</,,
I
L_j.JI7
7j_ rr _b
<.x U
?...-E
/
I
7_
84
o80<] <
\'t
J
t
J,)
t • i
zt t
t i t i t t i" t
! tp
t
< •
gL
o
t •
E
I ,.o
i"
m
°
8_
,<:s,_o80<1
\
oJ
i i _ i i ib
Ii •
1i • i iJ' i ° i"
Jo.i
i' i ° i °
E
SS
0
86
.O6
M
0.15
.60
.90
1.20
•O4/
CL5v /
. O2
S
Cm5
V
-. 02
-. 04
-. 06
-.08
L_-----------_ _ -"-'-"" -f------ -I----.-_
.I0 0 2 4 6 8 I0
NPR
Figure 14. Effect of nozzle pressure ratio on longitudinal control power and lift effectiveness due to pitchvectoring with a = 0°.
87
C
m8
0
Control effector V
0
[]
©
Pitch vectoring 0.0217
.0244o0072
Horizontal tail .2718'_ .3200
Canard .0970
f
,,,jr _}-.-----\I / u_--
-.04 /
-.06 O///
Reference
Current
13
10211310
/
/...-----_
Ji
-.080 .2 .4 .6 .8 1.0 1.2
M
Figure 15. Comparison of longitudinal control power from powered and aerodynamic control effectors with_=0 °
88
Percent sidewall
Left Right0 100 100
1.00 [] i00 25 1.00
FF.
I
•96
•92
• 88
:/( FG
Fi
•96
•92
• 88
.84 .84
I0
W___9_
W.I
1.00 6y, deg 0
•96
•92
• 88
.840 4
NPR
-I0
I0
5p, deg 0
[
-lO6 0 2 4 6
NPR
Figure 16. Effect of yaw vectoring by cutback sidewalls on nozzle static performance with cz -- 0 ° and 6v,p = 0 °.
8g
.0_
M - 0.15
Percent sidewall
Left Right0 la) l_C] I00 2.5 M -0.60
CI.,t
-.(2
.O4
Crl, t
.02
0
".04
-.02
.O4
.02
Cy,t 0
-.02
-.04 0
/
4 6 0
NPR
"i v _'E]
4NPR
(a) M = 0.15 and 0.60.
Figure 17. Effect of yaw vectoring by cutback sidewalls on total afterbody lateral coefficients (including thrust)
for A/B power nozzle with a = 0° and 6v,p = 0 °.
9O
• 02M • 0.90
Percent sidewall
Left Right0 100 100[3 lO0 25 M - 1.20
C[,t
-.02
D 13
.04
Cn, t
-.04
r_
.O4
.02
Cy, t 0
-.02
-.040
v ---8
4
NPR
C
6 0 2 4
NPR
(b) M = 0.90 and 1.20.
Figure 17. Concluded.
91
.O4
Jet off
Percent sidewall
Left Right© 100 100 Jet on
[] 25 25 NPR • 2.5
.02
-.02
-.04
.O4
.0_
Cn,t 0
-.02
-.04[3-----{ 0 [] 0 I
.04
.02
Cy, t 0
-.0_ E_._ _ :.--.O=:=
D u
__B_._._.--__-------._. t
-.O4-4 0 4 8 12 16 -4 0 4 8 12 16
a, deg o, deg
(a) M = 0.15.
Figure 18. Effect of yaw vectoring by cutback sidewalls on total lateral aerodynamic coefficients (including
thrust) at constant NPR settings with 6v,p = 0 °.
92
.04
Jet off
Percent sidewall
Left Right0 10(1 100r-I I00 25
Jet on
NPR - 3.5
.02
-.02
-.04
c , (3 :
.04
.02
Cn,t 0 C " -_ " 2 n
-.02
-.04
.04
. .02
Cy, t 0
-.02
-.04-4 8 12 16 -4 0
(b) M = 0.60.
Figure 18. Continued.
4
a, deg
12 15
g3
.O4
Jetoff
PercentsidewallLeft Right
O 100 100[] 10(] 25
Jet on
NPR - 5.0
.OZ
Ct, t 0 o " c 3 c _,
-.02
-.04
.04
.02
Crl,t 0 1:3 _ _'2 0 (3 [n
v
n
v
-.02
.02
Cy, t 0
-.OZ
"'_4 4
o, deg
E_:i, B m
8 12 16 -4 0 4 8 12 16a, deg
(c) M = 0.90.
Figure 18. Continued.
g4
.O4
Jet off
Percent sidewall
Left RightO lO0 lO0[] I00 25
Jet on
NPR - 7.0
.02
CI.,t
-.02
-.04
C O
.O4
.02
Cn,tE_Iv
D©
[]n
-.02
-.04
.04
Cy,t
.02
-.02
-.O4-4
v
[] c o (
4 8 12 16 -4 0 4 8 12 16
(d) M -- 1.20.
Figure 18. Concluded.
95
P/PLj
1,0
.8
.6
.4
.2
Top flap, centerline
NPR
0 2.00(3 2.50<3 3.o2
3.50rx 3.99
5.01
Bottomflap, centerline
P/Pt,j
Bottom flap, outboard1.0 _|tt_ttt_t_t_ttt,.,, ._+t,,,_ti!!!!!!!!!!!!!!i iiiii_i uiii.qi_.4¢11tttt#¢_:_.
_-_ !!!iiiii ui_uih_=,,,,iii_ii!!!!!!!_t;!tttt!t!tt!_[tl]iij H.u.,;::::::::r:_:::::::;::v.:::::v,m::v,::v, v,::H+__;;;;;_.........:::,,_::::::::::::::,,:::m,,!. ,,:;,.:,,,,,,t)iliiilll jii__iiiii#+i¢......... ,
8 _L_+_; ; ; ;;; ; ;; _; ; m; ; _LL_v'":: v' ""H :e_+_H'+'F_'m ; ;; ; ;; : ': ' ;:;LLLI_LI_
l_J,_ii4+] iM HilII M!!!!-'!!!!iiiiiiiii_iiiii_iiiiiiiiiiiilHiiii.:iiiiig;_
t_H:H_HH:HH:_::;:H H:H::H :::::;H::',::::_::::m::H H', HH::;H H H::_::H :H:'.W, HH+t
.6 :::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::
_ifi ilii::::iiii::::iiiP:iii::i::_iT/:::ii::i_:::iiii::iiiii ::iiiii::iiiii::_:iiiF:iiiii :/:::!!':!::_i_#:i_::_i_::ii:::_ai:_::_:qiiiiiiijiiiiiiiiiiiiiiiiiiiiiiiii.....................tt{+H HI :: ',',::: ',',: :: ',:H : ; : '.'.: : '.: '. :::::::_'_'_``_'_'_'_'_'_:'_`_:'`---_'_::::::''`_:_'_'_'_`'_;:'_'_':`_
• ]_:::;::::,....==:,,i-iiilMiiiilMii!,_=..!!!![!!!!!![!iiiiii.=!iiiiiii)iiifil _
ld-1: p i1H :]: ' H'_ 9 | f : H ',tI_H JlH li III II h,--'_,_ :N, ',: ',:',',',W,P,',:H H',i:i::: ',H ',: ',',',:: : ',h ,; }+1_
• _!!iFiilFiiiiiiiiii!!!'!!!!!!!iiiiiiiiiiiiiiiiil}iiiiiiiiiilt_t_' ' u :; ; H : H H:_: H ,,T:,,w, ,,,,: H ,,:_: ,,: H ,,:H ',,':H H :ll_t'H-bHH_H+Hi_fl
_++_++.+H_u,,, ::::: ,,. t,, ,,:::: :. E iE E Mii Mi i_ii H i ii iii _h.i_
I_IHhti. _H _fH_+i++{. :',',U V,V,:: V,; :',V,',',::',: V,::; ',;;_ fill il jill jj i;,+_,_ f_-m_ff
n 1_8_[_iii _i_¢_J_ rffff'il HHi L=h_ __ : m m _ __*_@8_1U .........................................................
0 .2 .4 .6 .8 1.0
H
lit
0
Bottom flap, inboard
.2 .4 .6 .8 1.0
x/[ x/[
(a) M = 0.
Figure 19. Effect of NPR on internal static pressure distributions for A/B power nozzle with 100-percent
sidewalls, 6v,p = 0 °, and a = 0 °.
lYPt,j
1.0
.8
.6
.4
.2
Top flap, centerline
H!tH_!
"t+r+'-:!
,++;'qltHl._fa]!X:!iiit
ti:qt*it
.4{+!+,il
"+;!!Y!
;I!F'?I i
H_::IU i
!!i_i!i!Itl:"!_;_::itb:;
::;i] ::
it_iii!!
NPR
O I.g9
[] 3.00
© 3.52Z_ 5.01 ! r_,,: L:._H
I 1!:I !_tt!t
!i"r::
Bolom flap, centerline
_/Pt,j
00 .2
Bottom flap, outboard
i_' tii
::_4;I
NN
*::" it
.8
jiiL,i
i!ii!i
H÷*-!
_f:ltllt
!q4;"'
t11_t
uvJ![f
+. ,_4+,,iAlb:'
x: ::
1.0
Bottom flap, inboard
(b) M = 0.60.
Figure 19. Continued.
,E_!i!_l;_iil'::it li:itid't;iilI!il!I_JrII i_
•i! !_A !i;__i_]A ;;:' _:_
[ir;;ii! :i[I':I
0 .Z .4 .6
iii ii_i!i, i i[
:tt! fiIfi ti _I!: _'I':
.8 1.0
xlt
97
P/Ptj
1.0
.8
.6
.4
.2
Top flap, centerlineNPR
0 1.98[] 3.01
<) 4.997.OO
Bottom flap, centerline
i _; t E ": "_ t +j
:F..+41
P/Pt.j
l.O:
.8
.6
.4
.2
00 .2
Bottom flap, outboard
.4 .6 .8 1.0 0
xl{
Bottom flap, inboard
.2 .4 .6 .8
x/[
!i_!!4h;_
!TV[
;ilHl
ittlH
1.0
(c) M = 0.90.
Figure 19. Continued.
98
P/Pt.j
Top flap, centerline
8
. ._ -. _., i__
.4
NPR
6 3.01I_ 4.960 6,99
,3 8.97
Bottom flap, centerline
P/P_,j
1.0
.8
.6
.4
.Z
0
0
Bottom flap, outboard
.2 .4 .6 .8 1.0
×/_
(d)M = .2o.
Figure 19. Concluded,
Bottom flap, inboard
__ .......... ': "'i: '_i::r 'i::ii_" i_"k"_i:_'_'; ii_i;L_iiii
.2 .4 .6 .8
x/[
1.0
99
_'Pt.j
Top flap, centerline1 0 ................... _;_;,_ - _ ..................
• _;_iiiiiiiiimth_M,,,:;: ............ !]i_ ; '""_
_"_;;iiiiiiiiiiiii211_i!!iiii_%iiiiilkiii!_iiiiiiii_u_ .................4f++_,VH_+_-_.H:!tHIII[IIII_ ".................................... ; ...................::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::: , .................. H ...........
• ==================================================================================== :x,_,-,,," ........
===========================================_;_IIIIIIIIIIIII;_ilIIIIIII_III:'I,1_
fi__ff_'f_t!!_t_!!!!!![!![!!!!?!iiiiii!!!!!!!iiiii
_iiiiiiiiiiiiiFiiiiiiii[ii_1iiiiiiiiiiiiiiiiiiiiiiiiiiiii_[iiiiiiiiiiiiiiigiiiiiiiiiiiiiiiii
_iiiii] iii![iiiii ii iiiii iii]i i]i!]iZi,_:'_.:iiiiiF,:_ iUiUilllUi¢_A
• q ......
_:_:i_=====H==========================================_:===========m:=;m===m:=='==.........
======================================================================
k_i_;;_]!!!!!!iiiiiii_E_E_iii_B_;;_]_i]_;_;_;_;hT'+.2_E_!:::::::_r -
_;iiiiiiiiiiiiiiii!!!!!!!!iiiiiiiiiiiiiiiiiiiiii!!!_ i_.2 .....................................................................................................
=============================================== ...... _1_ .
===========================================================================================
Ill I ::::::::::::::::::::::::::::::::::::::::::::;+:::::::::_ff_._mmm_IIll .......................................................................I! ...... :[::HTH::::H:H:;;;;;;:H:H[IHH::_,_"J+h_'tf_!_HH_!+fH_+ffI_[
NPR
0 2.00[] 2.51
© _.043.50
{_ 4.06
E_ 4.020 5.03
Bottomflap, centerline
Pl_f.j
1.0
.8
.6
.4
.2
Bottomflap, outboard........................... :::n:_n_._+_,,+_...b_bid_,_ ,_t_ttttt_
ii_;ii!!!!!!!_!!!!_;_!!_!!!!_'NI_r_1_]i_i_;::::_::::_: :.HH
::ilEiiii_iiiiiiiilEi;i;iiii_iiiiiiiii_::::iiiiiil]iii[IFill " , ...................._!!!iiiiii;ii;;;_;E_[_i_;_;_;_;_;_::::........................................................................................ _+,_:::::::::::::::::::::::::::::::::::: _ ::::::::::::::::::::::::: ............
:::::::::::::::::::::::::::::: ...... :::::::::::::::::::::::::::::::::::::::::::::
_iiiiiiiii!!tm_!!_$ti!!!!!!!!!!!!!!!!!!!!!!iiii]iil]iiu_::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::: ""iiiiiiii!!!!! :,,_?!_tff tf_ !
==============================================
==================================================================================================.............................................................................................. P,+_Ht
_iiiiiiiil]iiiii_iil]iiiiiii[iiiiiiiiilEiiiii!!!-_4_;; ..................
:m_::_iiiiiiii!!!E!!!!_!1!]!_;_E_!!!!!!!!?!![!!!iEiE._!iiiiiiiiii1iiiJ_+_4_i:_
___iiiii_iiiiiiil;_;iii_]!!!!!!]i_iii?iiiiiiiiiiiii[iiil]_........ ::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::: .......=================================== ======================================_!!]!!!!!!!!!!!iiiiiiii_:£_i]iiiiiiiiiii_iiiii_
iiiiiiill]i[]iiiiiii[iiii]i!!!iiiiiiiu2_-:;...... [:_=_[_u_u_u_u_tlliiiiiiii.iiiiiiEj!!EjjjjjjjjjjEjjjjjj!!:-:--_-_'_ijiijiiii_iilEiiiiiijiiiiii]iiijEjiijijl, _,iiiiiiiiiiiiiiiiiiiiiiii_._i_i_i_ii_i!!iiiiiiiN_ii_ii_ii_i_iiii_iiiiiiiiiiiiiiiii: ,-.'m ::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::: .......
!!!iiiii]iiiii_ii[iiiiii_iiiiiiiii[]ii]iiiiiiiiiiiiiiiiiiiiii_iiiiiii[iiiiiiii]iiiiiiiii__ltllt :-.Mtt! ......................... iiiiiiiiiiiiiiiiiiiiii_ii"iiii!!!!!i!!!!!!iiil]iiilEil]iiii_iiiiiiiiiii
It_ii!!!!!!!!!]!!!!!!!!iiiiiii!![!!!!!!!!!!![!!!!!!!!!!!!f!!!!_=========================================iiljjiijjijijjj[iiii:::l:l_================================================================================ ........
.2 .4 .6 .8 1.0
Bottom flap, inboard
, _ ,, _ I _ r _ _ _ a, 'F I [ ', I : I, rF ; ; I 1= rFi ', ; ', ; 11r, : : ] ', : [ ', ', : : 1, r, 'r ; : _ 'r _ ; : ', ', [ _ _ : ¢[ _ _ ......
_iiiiiiii!=:=:i U:::iF_::I:=F_:iiiiiiiFdF:::iii::i:=_i_d:dii:/:Fdik_:dii_
_,'; ;';]_ ;;; :; ;; ;_;]; [; ; ;; _]'r;;_] ;] [;;i;"z : :: I =[ .........
i
HHI ............................... ,,, ,, ,:,, ,H_+HJ_
_[i]iiiiiiiiil]]!!!]!!!!!!!!!!!!!!!!!!t!t_i[iiil[i[il]i _,]_:i;',_r_+t_
_!! [i_ _ "_i }iii iiill][i [] IiJi] IIi [III [; ; ;1:11 ;1:1111 :l ill 1::1; _i :1:11 "l fill: :t: II [I_l _'l I _':II "÷_+...... ! ......
_+_1:1] ......... IJH]H H H HJ_IH ::;_:1;:;::;::_'_' ' '; ' '" ': :
Vii_!':':!! ...................................................
HHIi-b_d ] ill;i:; i;;;; ;; ;il fl,,.,. '-_: ::::::_ E _E] ii _i] iE] _'_::----" ', !] i i] E i [ ', i] i i i ',i
t+q ,d H H ;,, ;H _: ,,;;:; :._=:,:: ,, ,,::: H H H ;::; H ,, ,, ,, r,: ,, ,, ::: H ,,,,: H r,: H :::H ::T,_ ::: ,,H ;:: ,, ::: ,,H :!
ii i iiii; ,,:._._..._,,::,,,,,,,,:::: ,,,,_:_: : .......................................... :1,_
iiii_iiJi!!!!!!!!!!!'!!!!iiiiiiiiiiiiiii';ifi iiii!!}!!!!!!!!!':ii_E_ilE[_i]Eiii';Eiiiiiiiiiiiiii'_*'_
|_!!_!_iiiiiiiiiiii!!!!!!!!_F_F_F_;_iiii!!!!!!_!!!!;!!!!!!!!!!!,,, ; ] ',] H IT] ',I HI ',I; H H '_] [i]I ......... b_c ffr_ PH+fH+H+i+fI+t+PH_ _ ._ !"
0 .2 .4 .6 .8 1.0
4[ 4[
(a) M = 0.
Figure 20. Effect of NPR on internal static pressure distributions for A/B power nozzle with 100-percent
sidewalls, _Sv,p = 15% and a = 0 °.
100
#5,j
1.o ..... ii !i!i,-:!Hi:fli_!_H*_,H ttt'Ht_+"
•8 _;iii _412
Ii! ili.ii,/,;: tt:l :2
• 6 _iil;{]ii:;_
III!I:-HI__7!i:7!17r!7
•2 _mt };n;!t*!i}tf{E:AHm_ID+V:Hi:!
_!!!!!_!!!:!
NPR
CO 1.99
[3 2.99© 3.52
A 5.02
Bolom flap, centerline
WPt,j
Bottom flap, outboard
i-tt
_ri*i. .n
t-H;t)fitf',:
=,.=.1_.iI÷,,i ÷H_
NN.4
t +H _ t+* t* _tl i ++;_4+i_b++4+
il 1ii _ : ::;, U_+l_A i711:}7712}111
.......
.6 .8
x/_
(b) M -- 0.60.
Figure 20. Continued.
.2
Bottom flap, inboard
.8 1.0
101
P/Pt,j
+ii+4)!_
IH:
H);
++++++i+ill
NPR
0 3.01[] 5.01
0 6.98
Bottom flap, centerline
i_,+i,!, tpt)*, i -t it tit ] ,,!Hi+m+
)_)ii))7j()J)_ !i+l_:m
:_Ui)t]7)t{))
t;4++i_ H+2)i4
++_,_,,Im::!r'i_!!i )_i!itii_iit,+=,+i
_ii]!i)il_!i;)_!.!]i:_:il i;:._i[ii
_+_+;':_ f::J iEi)!)i m::v: ::_+ •_:Eiii!!7 : 7T::!F
Lti!1_ ili;i)!it':::!i_+':ii%i!!i:+)!i:::;'.i
H+,_m _..d:.+q qi .......
!!H',_!_i_i!]!:;ii::i!:.Liii :_t_=_i+
plPt,j
Bottom flap, outboard1.0
++; _+ ++ ' +; " $_ + L 'P,,_ i"_ .... 1 t ;4 +
N
.. ++i_iliiHiH_;;+;,;;;;:i':,_.; i +:
0 .2 .4 .6 .8
x/[
1.0
Ii7+_
:iJ:ilii
i)ii
ilH:
(c) M = 0.90.
Figure 20. Continued.
H_
H+::
HR!Ii:
iiF;ii): !i
Hi::tiH, :_{t _HH! H
:_]!+!+!
+*+1++,+_+++.
;_tP!_tt
"_H':!F!FT
.2
x/[
102
P/Pt,j
Top flap, centerline
,.o_,_,_ ___i lI_il!f_ii__I_.... !_i__!_:_ii!!tiil
NPR
O 3.00
[] L00
6.98
z_ 8.gl
Bottom flap, centerline
_!h;!!_ _!II ;I I "_: __I'
_ r-_ i i ly ....... ]1 ".ILFmm_ti=!v,iF!}J 'i i;!ili!:Iti! !i;ii_:t i_!i iii
•iH;'= :ii i :::H :_
iii!#ii , _,;:,!Hi ;_i !H i "' .....;i!H i_!_ i_!1 ,;::E[r_;:;'_; i; IF F:
iiiiiiiii̧ 'i_i::il:jn:H
:i:i_iii_!i!ili!
**'li!!_ii!iii_!
ii!!iii_lli_!ili
_lli_!iiiiiii:i!;i_i!i: ;;!_4;_'
i_!li;i!i_iiiiilli!!;!Hiiiiiiii_ii
_ i!!!1!11_ iii!]!ill
!:!!i _:HH
::q3;HJ
!i!i!1I_;
#P_.j
1.0
.8
.6
.4
00 .6 .8 1.0
x/_
'i;hii
i,,_ ,
tHHm
*ilttti_+_iHh
!F;H!!_HI_t4HI
_i!i:iil
l;_It*t;
H,_'*m
tT:Hti_HHHII
0
(d) M = 1.20.
Figure 20. Concluded.
Li,
.+;H
t;!i:ttt;
_H
Hi;
.2
Bottom flap, inboard
'_Hi:!dh
i!!I!i_HI•._fH .H
:;diI ::_
;. Hi
: t$[,+
+_÷
,,r-- ,
i'4!ik
m;. l_ii:: iiii
:Hii.iH ::il
?m! itUill.4
iM.
+_.
F_!FI,b.H
i!Hi
ti::_
iH:L
Hli!
.6
:Hi: :!!::H
i[i]!!! ::_r:::_ _1:-i;_
U_:V;
Hit::_; [::11,:
:I'!!IV!!i_!! *_:,,;
..... ! _w+ F!!##i:_l t_!ttit_*_ i H,H .... mm
.... : ..... !:!!!:: Hi:!t
-, +-+!.,_. .:45;:H H,!U
t±J!itL_i_ ..... _lh-J_t_ ......[ii!!ii?..... ' .....
!iTT;i_ ::: ::: _*.n__,_;_hii!Ui_:_ :i'i
.8 1.0
x/[
103
P/Pt, j
1.0
.8
.6
.4
.2
Top flap, centerline
_Nm__N
NPR
C_ 2.012.50
© _.01_5 3.51
4.01
15 5.00
Bottomflap, centerline
ti.i ,k_,
I]ill!!i!!
1
I _ i:_15Hi!?,i_i:.t!:_::!it
; .....
.'t._tt ! -!
: qc:
_ .... i'.li_i]i|i:ii}:-;i!}!!-,_:I
_, " ' t :: ,A]_:;
P/Pt,
2 _
00
Bottom flap, outboard
.2 .4 .6
xR
.8 1.0
i;Hl'-I_m',:
] IEH t*_ ....
Bottomflap, inboard
....III.....iiiii 'iii:
.2 .4 .6
x/[
il l_I:%iill
ii ,,!!_i!}i
.8
Idl':Al
_!!t "y
Filiii
EE i;i
: ::: :
Iilii'ii"=ii
1.0
(a) M = 0.
Figure 21. Effect of NPR on internal static pressure distributions for A/B power nozzle with 50-percent
sidewalls, _,,,p = 15°, and a = 0°.
104
n/Pt,j
Top flap, centerline
-,t ,- t :!: ::i_ii!!:_tF:_li_HF;ii!ii!!i;ili!ii!ii;!!ii}i!iii;iiItA4AI_; _:_
}q,iiii !i_i!!Ni hm;!i _;iiji_!!i_i:_!!
"+_LLIt'_,.,LA;d 4 [I_'_
li_iiii!iliJ!Ci!7_ i!i iT.!ii]_li_liii7r__-!!i_ ...._",
!!i;,!!!-_ ;i r: qn:tflt + . ....
li.:::tt_ '.1+_ _:I1
_;_i;', /,,ii!_ii _i-;ti "+;_;;}!'!!_I:!!_:t"_! :t'+i:!H.........iiil!F_
0l]
0L_
NPR
2.003.043, 525.05
l!ii !iiii_iit!,i!ili
!li!!
_l!!is7ii_i!l
:1!t_ :;l_f_v:Jli k
,!!i]!t!I::!iiiii!
×/[
Bottom flap, inboard
_i:!!!7! !_:_':m ! q;
_Ai_ii;!i ;:.!'.f;!li::!ii.,....i(:i i;11
li'tt _;,{ i_:I;, !ii_!il_!li!!!ii::!I!i'q i:'_ IHI;:IiI_;t,;A 7:I_111!!mF:_ :
!iiilll li;_li!li!ll
II ;:!1 It} :! _il_'+il+'t :.:1"i
:4,-I !_!tii
O .2 .4 .6 .8
xll
:::tn::i {i!!i!i{
::M;:;4 i!q!:2':!!A!T!
"PtFH]E_i ;TL
i]171_71i
(b)M = 0.60.
Figure 121. Continued.
1.0
105
P/Pt,j
1,0:
.8_
.6
.4
.2
T.-:i_,_iF,,:_ii:
;!_i_! _m;;:,i_}'_i_I
....... im'4 :
-'!!_iN
Top flap, centerline
'tt_:" i _---4t_!i
_'>+_ _'
. +',!P}[ilfu_:
.......i iiiiiii i
!L:_:I .....
_,7l '-! t :+i _::_ ',i
mi_rJ;TT1
mlH;:l
:: ::: _JJ_T'q
it:7;H::
.... i}fi/il*44* _4
l!!L!_1i!!{!7
:!i_!
I!Y!,=!/1
,,+t_+
:!!i!=.Igll4"_!1
iif!l
:!!!!!:;+'1_i,.-4
NPR
0 2.04
[] 2.990 5.o4A 7.02
IHk'P.... :q I+ ._1}
!iT', Ii;;
t:::11I[L/II!::?_
;Til _7.'_ n.;m;;
]ii'::iNi::i:&7
Bottom flap, centerline
'ii_,l!!il::!!i_iit:ir_:!"+_...........
lN'@iii!_i7_7_7t:;!plr:;4:!i2:_ : i: ._A:L
:il;
iii !ii_ili! i iii!!!:I!!i i;ri:
P:TI_ ; b:i_
'_!1.:'tI,:_._: ::iI i#Ii'X_i!::,,_&kt!ii',i!i! i __:i:l, :i!:_
iI ,!if!++:: ::"u:;_l,_ _tt:tm:::,ilii;;i::_ii:_;_!i;:,!:iP.:iH:J:.!ii!_!ii!+!::_!x:
;,_.;_:ii:/}!:f!i1_;i_illi/iit!':i ::_]t:l[ii::i,_:
p/Pt, j
1.0
...... _ _:;j.....,L.I,
444_t4
H!tVt
ffltttt
*_!!!Hil
0 HMi "i ......2
Bottom flap, outboard
.4 .6
x/[
:wi.i i:iiiii!:' !+.; : !:;+ w:
¢?z-_t:_v,ii!:,!
_M _ ' _t_
i;_mJtt_: 2
.8
'x
fill+>12'
!t4H
14-_1
4f_
1.
Bottom flap, inboard
! ',v : ;i h :=_+_l,q: ! +:_:: ,+_,- H ...... ::Mi_:ii
. ii i+,, .%+iI,1_ :++ M,:, _:_ I+:+,1t' t !!!1
,:_;;;; ...... !Tit_!{Ul_i_,_ft;ii,+h;:l..._,-:
0 .2 ,4 .6
x/(
(c) M = 0.90.
Figure 21. Continued.
,+ b;:h i ...... +,
:}++i +i;;,+ !' Hi_. -41;::4;i
iff.. ;;_+i !:_il!':lh:: iU:_ L4;,., ;
fv_;ZAI;:
......{il'l.,+,i,.r_i!!!{il
},*._ :ii IENHN_I
:_ : : _ rt;;!tt,,; ...... Hh{7]l!l
1.0
106
P/Pt,_
1.0
H_
.6 _
;fix
.4 _
H+f*-
:_T_
.2 _
4H_:
Topflap, centerline
NPR
0 3.02[] 4.97
0 6.96
9.02
!I .........._u/.! _!i.;_: ::
_II :_, .....
::P_d .........
!:!,
Bottom flap, centerline
iiii _iii_ !itEi!
_i ,i!li
i:_il
P/Pt,j
1.0
.8
.6
;t_4
_+_
•4 trait
H+_-,
00
Bottom flap, outboard
"!.... !
N
.2 .4
xl_
(d) M = 3_.20.
Figure 21. Concluded•
_FZ
t!:!!
_k
F:Y,
I[]
[!;;
I!F
IiII
0
•_i ......
ttil !iJ_i.tAI :: ::
:ili :i: ::i
i;14 :!! :!+,
I:I_ ii
/d!_;
IIIH4i _ ....
!_ ttm_tt!glib
II'!!!_=_'!x: :
Bottomflap, inboard
' I:ii +_++,++_t_,+÷+
., _#Iilli
x/[
i[ !i ?
1.0
107
P/Ptd
Top flap, centertine
NPR
0 1.99[] 2.50<_ 2.99
3.51[_ 4.00
5.01
Bottom flap, centerline
1.0Bottom flap, outboard Bottom flap, inboard
.8
.4
.2
00 .2 .4 .6 .8 1.0 0 .2 .4 .6 .8 1.0
xll xl[
(a) M = 0.
Figure 22. Effect of NPR on internal static pressure distributions for A/B power nozzle with 25-percentsidewalls, _v,p = 15°, and a = 0°.
108
_'Pt,,
1.0
±:-!_{{I!i':i!!i .....
?i"i{l!{!......! :! [;
:_i' !!tL:!!!i i:: I{; :_i, _A:'
0 :A_I "tb :: }I;':
Top flap, centerline
' t*;_! ]ii;!!i
,., _li!I
_'>!_}ii!!iI_iliilI;li....i
_!iii!'_!__Li_[_iliii}!
li!ili_!i
'_!!i;_i!!AI!iii
_!Ii! [iiii! !:!,ii_[iv ,]1 --rl,:-{,
l_i]i'iii!iiiiili =;' iA t[_t*
: ili_* Ett*
i!ii!
NPR
• 0 1.99[] 3.00
© 3._o5.01
P/Pt.j
x/[
$+ii iiliiili
;;i{_:_ llI I!IIft t£ iiii_Ul _
44++4+4#-
N N
_t,_t .............
...... !'!{!_:iiiiiii
.2
Bottom flap, inboard!!:.:
++,44
',"H .....
.... _i
.4
IL d.
_+_..
x/[
(b) M = o.6o.
Figure 22. Continued.
109
WPt,j
1.0
.8
.6
.4
.2
Top flap, centerline
......... _!f:
I_ff__:-_l__ _ Z__:' ............
NPR
0 2.03E] 3.00© _.0_
7.04_ ¢_ _:
_-+,+
iiii!
Bottomflap, centerline
Bottomflap, outboard1.0
"_t fi_]iii'.:]!
:zH
; ,rlFi!il]iiiiiifl]iiiii_ ........ :
P,
•4 _!i +_
_ittN
0 ,2 .4 .6 .8
x/[
1.0
Bottomflap, inboard
x/[
(c) M = 0.90.
Figure 22. Continued.
110
PlPtj
],0-
.8 _!!?_i!:;
I:_ilf,_!i
•6 !j;i!:!;
.4 _!!iii!_i
-,!!7+!.2 C!!i!_!!!
HFPHF
ql:!!!
!!T"!fT
Top flap, centerline. . ..... . ii_,,;!,;_ ,_,1 !_iiiii_ .....
i iii .... :'"* . : i !i!!l_¢_i
!ii!!!i!'_!illiii i';l!iii ii i_ _, ........
::!f_;:!! _,_':_ ......... mm_;:
+,H ,L .......
NPR
© 3.02L_ 5.04
0 7.04L3 9.01 liJHHd
Bottom flap, cenferline
!lii'_!! :!.+ri
i:,tl,_, t
EKTF:!
P/Ptj
[7 ::
r_t'ff
:1 '1',1[7
*!!!i_
.2 )li!!ii_
0
I::_ I:
!T'!tttt
®
N_
'_F'!tt!
.2
Bottom flap, outboard
iN ':[ _,
_ :rW_ :::: ::
lfii_i i!IF;:.i!iF!!tl *_t
4 6
xlt
_iiili_!tiilltTltt_r
mtt!H
iii:':
fft_ifttthT_t
1.0
(d) M = 1.20.
Figure 22. Concluded.
Ill
Cp
I nboard
ii!i!_Li!_iii!ii_
0 ii}!i!+!!,?_!:hiiii:
'_ i_i_t_!_ i_!NgN_U_ !_
NPR
c_ 3.01[] 4.%©_.m
8.97
Centerline
M - 1.20
_i'; !i!i( "/_=" ......... ";_
;Z!_il_,;:_i$:!+(i!=:i!w!!_it!U_:,:i_;)il
Outboard
F_i))i)ilEt)i)i;r1+['A:llm_:t;_
i ii!iI{i!i!!i)[::i;)){li))::[))ii_tit)<_t))i:)_i
'. _:{t:ll;:l_;l:t;
!)i_!:::I_)fi!)!)_i)l_)_)i;Ii:(iiiii_!}iT};;;!ii_,{i!_¢_'7:!!{
iiii_iiiitiiii_i{]
:till:r;', !_i!ii': q:_. _:):I t_:t:*t_
!f!i!!i!i ....... i )I_ ii;i_;!_iiiii_! ........ '.....i_i_{!!{! :,..v_ll- "-b'-;:,:.l:Hi;:i:d*d
ii!ilil iiii_!!ili_!_:!__*)_i}i;{!e {;!!i!i{
CP
• 4 _f;_
0 _m_fl_il
-._g
_._ I_i
N
liiif!if_
t:t]:l:;
il)))
11_;E!i
!_E)E;ru v-,
iii!i;i_
">f-!"
._.II[L
h!):i)t!'t'ti_
h,l I_,
EI_IIEil))::L!l
CP
g_
-.2 _}+_
))_)I
-.4!!
ifiU:_:tl
);iT
0 5
X/L ×/L X/L
Figure 23. Effect of NPR on external static pressure distributions at test Mach numbers for A/B power nozzle
with 100-percent sidewalls, 5v,p = 0°, and c_ = 0°.
112
CP
I nboard
.4
_/F:ili :Nil>
!iii!iiK!]i i:
-.4
-.6
NPR
0 3.01D 5.000 7.06
9.03
Centerline
M - 1.20
Outboard
2:hb: ::n::h:: I : L;!:i:__i,:<i::! ii:i
r;;N _-:w-'
:2[Ni!i2 !i[h!Hi :_ :;:_
CP
,4
0 ;iiN!i;fi!Nili< ;;;:3!LJN_i!:!Ni;;!:_I!H ;.< .........I! t_'::_r:_:!j:H:l:;r K!ii!_iiii?__ !!:t!Hi .: iNi_
,_z_:_:,.......!i;;_i!il]!i!!l!::::_: i!i!:H-. 2 _:_:H;;:I:N:N;h _i;!_]ii] ii]!_t_;
N!i!i]iNISil !iiiiiii __.4 !;!ii!i{iiiiiiiiii
...._::,_tj<ilHiiiiiiii!!i_
......................!:,:N: !/;!:i: ih-i i:_¢_
h_!EN ....... ::::w :::::_:
oC}
0
d_
NPR
2.02
3.004.99
7.01
:;_:1:_ ;::_:;:r _ i
::F::IN!!Ruii [iH:Hi IiiHEN
Si!!fi
iiiiii!i_i_iiiiiiiii!_iili?i
Iiii:i!! !ifiii_i !ii ilil!ili
,;:,,,....., :_ii!i!!ii!_!iil_
_r:h:;- :n::;.uili[iili'::"..........:;]:t:i!;:r_
......... S?_i!;t mt:w:: "
CP
_i!:N ....FN:i ;!:!!:::iiiii_ii_[NW
o ii@i{!
',@ii!i-.4[!!!;Ii_"_if]i}i]!i!i!;]ff_ii
f:N:::;=N!_-.6 _i@_{:!iiN]i!
O l 5 ] , 0
x/[
00
©S
NPR
2.023.013.58
5.09
I_i[::iiii i i@i] f_ii
I::!i _; '_r_!l!it::........ ;!Nii
[i@{iit{!i:i:;_4<_:_:*,_i!itlii!i :!HH!
iiiiii!)_,;;!is_ii;ffi !i[il!Pl4ram F :H{I_ iti _i!!
!H_if :;liliW [Nil{'_}]_ [i!ii'/F ....i:'::<:!iiii!il '_!fiit]Iq;,+
-1.5 -1.0 -.5
M • 0.60
_kN:i!
!:!<;_ iiii:il!_i!!l:lq :.r:;_:_
!!ilN! ;
!1i!;!!i@II!Hi!!i'_':!'_:4!:#_......!i!i
Ith_:H _ li ii!!li !i!i!i!iii!i!!i!ilill_ii!ilillI:HNH'HN:_:;
iti!;li_] i; iii_!:
1fi!;[_h!;1!t_',y ] N ]l:]]!::_liEliiq:N!]P:F q :[:: :
l_,i!i!!i!I_,S_i;
5 10
:i:
0
_ii ii!!_i_ji_iii!!i:
ill Ji ]F,i[iil_[iill.J;q,..: :]_!
""**++tHtf;h*_
I< .........
tH; f-tFii!i-i::F!!H! :::
H+,i_HiHii_i!
_fi:H: :_:UHt
1!_Ii%81_f: :;p.ll:H:,:n;t:L:]:l]:i:;[.]'I!!]H£t!!r i!h:
: _iItli. !F1. .!., !.L.,i.
_HW|I i NiH
i_!i!}[ii:;/!:in;lu| : ; , :i
.5
X/L X/L
;;_:u;t
!* i}!!_
L!<
N::::I:t:t;;:':NH:b:151
:_<>:t
:i
I nboard Outboard
CP
.4
-.2
-.4
-.0
!ii_,!i=_i}tie
ff!!:Y) !!):!!
:,1:-5;N
JmiiH;
:__:!i_
AE!.I=,!t:dP/:
+,+-h*+.
i)ii'")!
HH"_H,
ii)fii)i_)
:i!:?ih:
CP
:"'_I (iilm
-.2 _liiR)_ :_ttLEt
reI_4_H -.
-0.90
....... _,_2.03 _,!_, ) !)}! ..... iF.il
-, -_, h iFi{i+--_+ _++.,V;t;_ttt; <> 5.03 i_t_i_ ........ ]i@h h_ff4# !##_
.......... biiH:l :vr
ii!i)i}ii: +:!')l:,il !÷iit_!:4:! :i," [_ _ -_ _)-IU
:!!_!!!!:! : ........... _i<_Jilliii -
....... ' ,:vt : I,÷_H
:=_=;_ _ iK ii}iiii_E;i;i )i)Hiiii::_*_,:_+m+k+, iil;]!tH :: : : ;:_id iH.iii_ :m_
..... U_.4)! ................ FF:Iq: :I};: ............... I <:t;: .... ,.,
.... khd
_Ji{igl_!i!il;t",,U
_*+?;i'Itti'i
I_b,]i ;i!<i iiii,ii
i)]iFqT_ :!TFi:;h;iTEii;,..,,. ,,.. h_HT:
:;til
-.h!
!Hi
:m_::
d:h;::_ :iiii6)} !};E)_
i:!!q
,.:iiiii!l
CP
+44h +
;ii[ili_
]:)]F:T_
_tR't
N
:.:.:..:.i :.:.
4+.++,+_:iFI;;ZF
IKh_F:
!))iji;_));
1.0
NPR
'2 1.99-_ 3.00
© 3.54,,,_4.9/
i-HH4-
N
_HHq_
*_N4*i!.+JI)H)))
: )
ITF ]:H
i:iii:::::: :
: ::::
:!'!7
-1.5
M -0.60
:11_ I:_;_;:i;i i: ".::':_!!_
,!+! H_r_HHI l,+i _*}H-; _-i
Fb:_ : ::: ::: ,I -v up, H _::: :
........... :t!:_:il i I:,,H ..............
-1.0 -.5 0-.6
0 .5
X/L ×/L X/t
bll;t
!i!tifl
bli!i:
.+_
!-_y.
:?i,i
!k_:)
:n;
1.0
Figure 25. Effect of NPR on external static pressure distributions at test Mach numbers for A/B power nozzle
with 25-percent sidewalls, 5v,p = 0°, and a = 0 °.
114
CP
I nboard
.4
!il!;iii _",i_::_,, i_ i:¢.:ii!iiy:_ill
?[:ili_:!l?:iqf:_ :iHil;iI_i!_ i:
:fill!i_i;i;iii!!_il:_ii:_-.2
-.4
-.6
NPR
O 3.00
5.00
© 6.98
8.91
Centerline
M " 1.20
:m:_:_: i_!]i',:! : :: :; :.: !H:::',i_l: _[! E_ ;1_!! :i/H !! !_ !
i_,:_1::,,,,, if! !!11+!:i:i!i:J!!i_!!!!!!! I !:i ii!illi....................
....... :i::l:i:r iili !:if!!:! -:<:}I_i! i :1 i ! _ : _! !i_
i] [ii:: iiii:i]i! .... ih::j:::l::i:_ _:ii:h_ |; i:iiii: ! _!_:H : _ : : :i_i!!l!:_'_':_'_:ili!iiii__.ii!ii ,.......I, -..... ,.....
i:1_i :I:H !:_ dq:_', 'W,4h:H I:,V!:!:I:H_I,I_
m ,._-_ q!i!'4!
i:ii i:!i !! ili :i!i.!ii!iiii!ii!iiiiiililli
Outboard
........iiiiiiiii........,.........ii!i!iiii ..........._....:m:l_ !:
_:!m'l :i!!_i]_f! i_:t:_:: ::tin:t;::l_:t:i ...... {_i!ilU!
i!)il;!ii!!i!!i!ii!ii_i;i:i_i_ii_ii i_)ii iiii_ :i:iriil iiiiii!;i
£Z:! : ;Y _:
:i![ii!_i!fiii!!ii;.!!!5!!!J!!::!!:!!f_!i?;!.ii;_!:Ti::_51":i:::isiti?>::r:i
i_i:illil........... !i!!/il ......!!!ii !:'!Ii:H:!:_IiJ!!]:K'!Y]_
!i!i!:iii iiii_ii:i_?i:i_iU'ljYji2::i
CP
.4iii_iii"'i!iLiliiii:i_ !i!ii!+
:ml,_t_.__f_::I:!_i!! :!i::1: :Hi!i!
iiiii?!ii!ii_ii;_":ii:i_i
-.2 !;_!iii?',r_;_:_:t:til!ii!!
_Fi:[:i*:i:::?_!
rt;i:t!:il!_
ii_l!ii_it!_iiNil,,..=i,i.i......T_:_:H:_ I:;::hh ii_i!!ili-.6 ....._4.........!i!!i!i_i
NPR
O 2.003.01
0 _.01,_ 6.98
M - 0.90
!{;!_!_ii!E!ii!!!i::!m:r _:;:;_:Ui;::lil:H;;::;;!:iii!i!iilUi!Z
i;tiHslim::m_
!i!_i!i_i::::_:i_:..... ifi!i!iii
ii :iiH:i: :H:Dri
i!iiii!!!ii!!l_Eiii!i!ii;i;i!:iil
....... _;_:n:t:_H?!!iI_
?_E!il:i; _!;_H!]
T_i_mrI_:[:ii i!iii,!T,_:i!sr!siiiiiii!if:._:i_;; _iJ!!i!'!Ci_iiil
CP
.4
.2
-.2
-,4
-.6
NPR
0 1.99[] 2.99
0 3.525.02
M • 0.60
i ..... ;_h_:k,t ...... i_il: ';i]:_ il:.iii
t:n:V _:i: Vl'i!: I _ t:1_;] I
, ;_,i_ii!il::Ii!i!!i!'_!ii?ti]!i!_]Iiitli:iIHi_f!!ii!i_ :,_..__*
_I :""" ii_!iiill:_!_I,_ i;tii! ........
Ii:!lr_:_.I:: .......:_il;ii
_ i ,!i:ii!:ii! _5_iri: i!_i:!:I,TIIU:_ !,i[ ! :i: ',i
-1.5 -1.0 -.5 0 .5 l.O
:if[ill
_!:!E!;
_:i q.IIH:
i iii
:tl!_: i:4:u:!::i?!:!i!
,:iv-:
!i! ,_ii
i::i:i!i!
0
::_:_ i !:!i [
i:i_!iiiiiilH:ii_i"
!_i_ H:_,,,....
!_t CH.i
;im ];_- ,
I,,,:::: :i!!q
!!i i,
" Gi{_
1;72 1!:1n11
::ql .:_n_!!F [ !:]!:
.5
X/L X/L X/L
:Wh:l
:;:f:_::!
ii!iI_[!H; -
!I:H_E
ii:ilil;i
,-_r i
0
Figure 26. Effect of NPR on external static pressure distributions at test Mach numbers for A/B power nozzlewith 100-percent sidewalls, 6v,p = 15 °, and a = 0°.
115
I nboard 0 utboard
CP
.4
.2
-.2
-.4
-.6
.........i!ilb+44+i!i_m i i!t _ii_i
!zmii_:i!_!i!_iiH.,..7t
mm:_ _ ....,
!isA-
NPR
© 3.0_
1-j 4.97
C _ 6.969.02
iiw'i!!!i IIHHilI;I;I_:i
H_iiii_i!i!l_!ii!i!ii!¸i::ili_iulilli_i_
.._:,_,4!i;tilitii:iFiiiii_!lifiH_:,%lii!,i',!ii
_ !_i_m!t_il_!.................
Centerline
M - 1.20
.......L:liH-_!m:!_ iii!ii!ii_,J_.J_k
.......... ._.
'_+ ! H'_"_iICC_ ,, TH:ITT]lIl_,
!ff+'fffffttt!ff+t_
iQ!: 7¢TT.... :Fbm_ i'T!tt_ i
¢i _!!r,@li]_
!i:hi;;_!+!i_il
_i!¸!i":i![_f[_1_i;
cP
NPR
© 2.04D 2.990 5.04
7.02
i_I _R_.
: _hgHlN 'X*?_?
...........xxxh; ........
H÷+.++
"" }Hi _;I .......
NI -0._
H_i_#_l_!it;_:_!f.:_ : .......
::: :::::::::: :: ;u: il
:ul :LI'"' _trr_.
NN
:C:I;I'::: :::: xxx .....
'.i.hd-
!11!ii,Ii_14;
i!]!!:T:i_ii_i
........:!7i!17i'7/i i"
!!!i........
x:, ,, ;4x; ;,;
, .... ii_t!.m_il....
............._,!iH.... : !_!!! t!_'
!!H}! i1_i:i:......... 11"t_
i:i:i i=;Nm_m_ mm
::: :: mm;:_ ,t !iriS!!
:" i!!i!HIt;!;N :t_ IieL!! :::[_
nm_:
,H u_
x bx
,m-fff!f
CP
!i_i_¸ !_!_
0 _i:c.1
:711[_:,i_4i__;:._.¢_t¢..}iti
-- 6 0 ........... [ 5 ............. 1.O
NPR
r) 2.003.04
3.52._ 5.05
-0.60
:: ::::::::: .....:::::::
_ ::::::::::::
!T!if!!!i _+*_++
....... "'_;?+tl
t*'tt;_ !t ,,***t,_t
0
a_t
i_+]i
B_J'_tt'
!t!_!
ttP,_tt;) .........
1.0
;:tti iNSi:
Immmli!l{i...............;111145;:
itl!i!i!ta!t__!_! i_ ,i •
i ':ill F :::
!!T![!;1;!!:!:! i_i;_
_i_Ili!l!lllIil4,!
0 .5
X/L X/L XlL
_umx
,:x: ::
-@ttH++
N_<]tm[
PJ[II_
_ki?li[
].0
Figure 27. Effect of NPR on external static pressure distributions at test Mach numbers for A/B power nozzle
with 50-percent sidewalls, 5v,p = 15°, and a = 0°.
116
CP
I nboard
;m:u:1:H:;v: iv; im_;v::;_;i:_Fi:;i;_uqiSPm;:
i!!:!i:i!i!i!H:i!i_!:l!h:;i!!iii[!_]:!Li-i:H:i_i; i;:iK_!; ;i[ i_!:;c:c_ !i_F!!! i!!:!i]i_-ql;i.]
?iig!Fi'_:!:r--i : I_r::
0
iiiiilk!i iiiiiii; i:_: _>ri_i
ii:!i;iiii])!!2;il;itii:i!!i_;i!;_i_
-.6
©0
©
NPR
3.025. O47.04
9.01
ii !ili! ilili!:!.iiLi_ i{_iili
_i_iJ!iii!iiii
ii!ikiiiiii:i!_i
! +!; _;:il iill
:r::m: .......
iiiiiiiii.........
;::r;:;
i_mi:l 119!!iiiii!;! iw,i_i
Centerline
M - 1.20
iiiiiii_ll ii!:ii:!i_iiiii!ii: i1111111;ii_ii:ii"[_i;;i.il!i_!iii_H:i_r i I r_::_::l:_::'::: r_;:::_ :::i::
,,,,, 'iii!i Ii ;"" 'i!Li!ii ii:!!ill/i ;/ ::iii!!ili!iiiii _
i;_!i_iiiiiiiii!ii!!:!i:i !![iii _:
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!ikl:iii_
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: :i_: i 'Li:im iii!Cfi"i I!_;! ''
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dii:k _i!!!H _ _ .liii:;:_ ;_
w;h!!ii i_i'iF, m_:;;;
Outboard
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=Li!il;,_il;ii!!k!!Z!i;i!i;i!
i;iiiii!;!iii__,:.,_i!iiii
:,,,_ !_iliJ!i'_iii:fi'i:iii9
CP
l i!ii:il
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ii IE[I :Ti!|[ :6 ;]i ; :;:
-.2 " 2:A: d:
ii!: i:21: if!k::
-.4 _iiiiI;:iilLiil;:I _:i_:: !i:iF:!?!ir
r.;:, IL::L r:
!fii!i_!!i!;/! :i,:i::r!:'
NPR
© 2.030 3.00
0 _.01z_ 7.04
ii!iw_
_ililiiliiiii:iil!W!i:1:, :_:
2 :;_:! _ffl:i _
!ill:i; i i!!i:il _¸I!H!I!]i::r:u_imli:
Ilifilili!!__iii
ll_ili!;ii_iLiill/i
_ii!l:iii ii _t!!
il_!il!i:!i ;:i_i
i Tml:l
!_i_!E!imi!!
ii!ilii_!I::l:Jiii:l
4b_:HH
M - 0.90
:.ii!i_llii!/.'.i!_i!::::iiii:!i_i i:._i]_!!ii_:ii!::i'.
'!'! IH q: '.ii! IHH!!!!f!::!::tii !ili;i!il qjmm':Im :r,;!t ;.................
, _ iv: !']:[ t [ ; = h:[,f, .L "
iii:iI :';:!!mll_TH_ ..,h:MJi -'!_ ! J:
: :q;!!_$Ii:.!_ ,;!_li!i;ii;_ ii!iii!......_:
iiii}:!iii?i}ii!i i!!iili!itili !i'i'!'ii' !_liHi ! i'_t!1 !m" !*_l_i] ii::I _i :El.....! _,!
!mlt!_ :iit!l!_ :f_; I_;,l:l:,:,v,:_
!:I:L_ !ii_i_ii;i,_ii_!::!l!iii:;_il]:;!i._;i ii_!':i;ili_;'i;ii:i!i:
!ili! ii:i]!ii! i_iL!!: i+:]ii!ii
:i!m:; ifii!k ;:.:., _.........:.t rl I_:lt;c'._ ti:t ,.: ,_!:r _,:._;:i::i_.-',ii!i!i :ii U :i:i
CP
.4
-.4
NPR
0 1.99[] 3.00
© _._oz_ 5.01
!iilii:!!
i!i!_ii!i
!:!i_!;!i
_ili!i!!i__il!i_!::i
:iiiii!_!ii:ilYi i!
q !'Fq
• _i_ _ i!
i !T:;!
-l.5
M - 0.60
F rq_ Hi iii
i: :r:i
-.60 .5 1.0 0 ].0 0 .5 I0
X/L X/L X/L
Figure 28. Effect of NPR on external static pressure distributions at test Mach numbers for A/B power nozzlewith 25-percent sidewalls, 6v,p = 15°, and a = 0 °.
117
Cp
.4 Inboard
iii:![![iiii:[iiii[I[i!iiii!i"_:",_,=
_[]::]]!{[]H ;]][!]::[Ll]]:;::
........_i_iiii{!i!iiiI!![__T![[ilii: :[}H_
0 .5 1.0
X/L
NPR
i.97_ 3.01:'_ 3.55,_ 4.98
Hf_:;:tt
!iii
H!I
t!!i
-1,5
2_-percentsidewalls
Centerline
-.5 0 .5 1.0
XIL X/L
1.0
CP
.4
.2
0
-.4
-.6
h[:i U:' :: _ii!! }:!E_iEi_;L: !]:_ :!_ i_111 H:;'.,
[;;I?T i!1!!::I *:' _i
I_'::: ........ I ;H!II
}!i!iZ$ :'_
Him:: :!_ii
.;_;,. !iilI!ii!_ ;tlii;
iii_.:_!Hiiii!iili ii!ii!
iiii_,:: !_!!:,_!t_ii ;i_iti
_,J,,
® !!!!.5 l.O
XlL
NPR
0 2.023.053.51
5.01
ttH
_dJ
!ii_g
H_itti_
mh
_rSt:
-1.5
!!:!:;. 41; :m_
.......+'" Uh
.... !!_!!! r! ;, ;.....
:: : : _ii_
0 .5
X/L
;if
1.O
Figure 29. Effect of NPR on external static pressure distributions at M = 0.60 for A/B power nozzle withcutback sidewalls, 6,,,p = 0°, and a = 20°.
118
CP
.2
-.2
-.4
-.6
-.8
Inboard
NPR
0 2.03[] 3.01
0 3.51L_ 5.00
-1.00 .5 1.0
XIL X/L
;Hf; -"
71_!!!ii_ i!!lx;V:
ii !tH
P4H_t_
tVT_itl
h ;,;
;HHtf_
-1.5
25-percent sidewalls
Centerline Outboard
!:!;_i!H!]..,! _ .:=:miii!_H!t
iiWii_il;i!i!!!! [ !=;_
]!!iHIt :::::m ::: :i _ i:i:::!l
i;i!iii?i_iiil!!_i _i!ii!!!......... H I ";;;iiii!i!il::_:'_:_iN!_!tii_iiiiii
!!!!m_i 17!
0 .5 1.0
ML
CP
i ., 0 3.00 _ ]F;'-W[:m:::: H!i_iiii
l i!ii ........'......;-.2 i1::i P 0 3.54 ......... u::;4t i;::Ii]i
!:::_.U iiiT!i7 iiHfiqi
]]:ili_'_ :i7 ,i:_;!;,,iii__ l,_q!lr!r!t ,£!i;iiii!I _:;: u P!!i! 7:i!!1H7i;i_i P =:=Hi_4:i_71111![i :;::_h:mu,.ril:_: EiE;!;]H
i;_i_iillT!! :.:m,:
ilqti_i iiiii;_; _j!iii!lmim_ .....
!!_i_i_! - ;m; H]HTil i i;;;7!i[
-'6 iHW!_}_!ii!t!Ii_tli.... _[!!!iHl!i_]_iIii+' m ,::: _*,!'1_::i_lil;ii........._;::;tr14 1ti i!H
m::'+ :'+::i _!:;im:: I l!ii!i!I ii!!!i! ........!
_1ii!1_: !11 ::;f] ................
i !::!i;
m!i_;:; _iiiiil!!1111!1-I.0 _![_;.',:_i !f!ili _! :'.:i:!:0 5 1.0 -1.5 -1.O
]O0.i}e rcent sidewalls
iH : iiii!!!!iiiii!il;
P, ;P: _ :::' : .P1
171_;F:u
-::=:;f !!u::-U Ni
!i!!iTiilH_IfY?Ii!!
iTi!!illi,97;iiT!i,i!i:.i!, :: .::::
ii_iiiii!i_iii!iIi7iiiiiN_immlifii!_Ii#i!l! !_!::;mi: !iiiil I!;;;:_; ::Mlt:x
0 .5 1.0
X/L XIL X/L
Figure 30. Effect of NPR on external static pressure distributions at M = 0.60 for A/B power nozzle withcutback sidewalls, &p = 15°, and a = 20 °.
119
Report Documentation PageNall_r/_l _erunaubr s and
1. ReportNAsANO.TM_4155 ]2. Government Accession No. 3. Reeipient's Catalog No.
4. Title and Subtitle
An Experimental Investigation of Thrust Vectoring Two-Dimensional Convergent-Divergent Nozzles Installed in
a Twin-Engine Fighter Model at High Angles of Attack
7. Author(s)
Francis J. Capone, Mary L. Mason, and Laurence D. Leavitt
9. Performing Organization Name and Address
NASA Langley Research Center
Hampton, VA 23665-5225
12. Sponsoring Agency Name and Address
National Aeronautics and Space Administration
Washington, DC 20546-0001
5. Report Date
February 1990
6. Performing Organization Code
8. Performing Organization Report No.
L-16563
10. Work Unit No.
505-62-71-01
11. Contract or Grant No.
13. Type of Report and Period Covered
Technical Memorandum
14. Sponsoring Agency Code
15. Supplementary Notes
16. Abstract
An investigation has been conducted in the Langley 16-Foot Transonic Tunnel to determinethe thrust vectoring capability of subscale, two-dimensional convergent-divergent exhaust nozzles
installed on a twin-engine general research fighter model. Pitch thrust vectoring was accomplished
by downward rotation of nozzle upper and lower flaps. The effects of nozzle sidewall cutback werestudied for both unvectored and pitch-vectored nozzles. A single cutback sidewall was employed
for yaw thrust vectoring. This investigation was conducted at Mach numbers ranging from 0 to
1.20 and at angles of attack from -2 ° to 35 ° . High-pressure air was used to simulate the jet
exhaust and provide values of nozzle pressure ratio up to 9.
17. Key Words (Suggested by Authors(s))
Longitudinal control powerDirectional control power
Thrust vectoring
Fighter aircraft
Twin engine
19. Security Cla_ssif. (of this report)
Unclassified
NASA FORM 1626 OCT s6
18. Distribution Statement
Unclassified--Unlimited
Subject Category 02
20. Security Cla.ssif. (of this page) 21. No. of Pages ] 22. Price
Unclassified 120 ] A06
For sale by the National Technical Information Service, Springfield, Virginia 22161-2171
i
NASA-Langley, 1990
BULK RATEPOSTAGE & FEES PAID
N ASAPermit No. G-2 7
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