View
217
Download
0
Category
Preview:
Citation preview
8/12/2019 ersen nyilazott szrny orrsegszrnnyal val aerodinamikaihatsa
1/70
,4",_Ck / 7z ,.,-z/
NASA Co ntr acto r Report 172531
NASA.CR-17253119850014054
EFFECTSFLEADING-EDGE EVICESNTHELOW-SPEEDERODYNAMICHARACTERISTICSFA HIGHLY-SWEPTRROW-WING
SAMUEL, SCOTT, ORAN W, NICKS,AND P,K, IMBRIE
TEKWORLDOMPANY ' "-_"
HAMPTON, VIRGINIA1,'I..':i' "c: ,, _,. j,,.
. a_ ., _ 'd 6JI; .r_ .-_ 7
PURCHASE ORDER L-69215B
FEBRUARY985 _i_r'_ _ __r_.r
: ',i ;_,50
tJ-,NGLEYRESEARCH,:EN rERLI_.RARY,NASAij : r. "'_T('_pJ............. VIRGII'IIA
I IASANationalAeronauticsandSpaceAdministration
Lan gleyRe searchCenterHampton,Virginia23665
8/12/2019 ersen nyilazott szrny orrsegszrnnyal val aerodinamikaihatsa
2/70
8/12/2019 ersen nyilazott szrny orrsegszrnnyal val aerodinamikaihatsa
3/70
CONTENTS
Page
Symbols iioem o mooosmooo o mmomoooomm e IeooamIo
Summary .................................. iv
Introduction ............................... i
Model ................................... 2
Tests and Correction 2ao, o oooooeaoeeoooeeooeo, . o
Presentationof Results .......................... 3
Results and Discussion .................. ........ 4
LongitidunalAerodynamicCharacteristics ............... , 4
Effect of ReynoldsNumber .......... ............ 4
Effect of Leading-EdgeVorticies .................... 5
Effect of Simple Leading-EdgeDeflection ............... 5
Effect of Leading-EdgeSlat ..................... 6
Effect of Variable Chord Leading Edge ................ 7
ComparisonofLeading EdgeDevices 8me em,o,,o e ,, o ,oo,
Effect of Trailing-EdgeFlap Deflection ........ , ..... 8Lateral-DirectionalAerodynamicCharacteristics. .-........... 8
Effective Dihedral-Derivative ............. ....... 9
Summa_ of Results ......................... .... 9
APPENDIXA .......... ............ .... 10
References 26o ,oo,eo e o, oo o , e eoelo,oeoooo e ,ooo
Table I , ................................ 27
Figures .................................. 28
8/12/2019 ersen nyilazott szrny orrsegszrnnyal val aerodinamikaihatsa
4/70
SYMBOLS
The longitudinaldata are referredto the stabilitysystemof axes, and the
lateral-directionaldata are referredto the body systemof axes as illustrated
in Figure 1. The moment referencecenter for the tests was located at 59.855
percent of the referencewing mean aerodynamicchord. The referencewing area
and referencemean aerodynamicchord are based on the wing planformwhich
results from extendingthe inboardleading-edgesweep angle 73.02 and the out-
board trailing-edgesweep angle 41.46 to the model center line. (See Fig. 2.)
The dimensionalquantitiesherein are given in both the International
System of Units (SI)and the U.S. Customary Units.Computer symbols used are
given in parentheses.
b2
A - aspect ratio, Sref
b - wing span, m (ft)
Drag
CD (CD) - drag coefficient,q-_ref
CDi - induced drag coefficient
CD - minimum drag coefficientmin
CDsym - drag coefficientof the configurationwithout twist andamber at zero lift (seepg. 4)
CL (CL) - lift coefficient Lift ' q--_re
C_ (CRM) - rolling-moment, Rolling momentqSref b
Cm (CM) - pitching'moment coefficient, Pitching momentqSrefC
Cn (CYM) - yawing-moment coefficient Yawing moment' qSrefb
ii
8/12/2019 ersen nyilazott szrny orrsegszrnnyal val aerodinamikaihatsa
5/70
Cy (CSF) - side-forcecoefficient,Side force qSref
- referencemean aerodynamicchord, m (ft)
q - free-streamdynamic pressure, Pa (Ibf / ft2)
S - Leading-edgesuction parameter
Sref - referencewing area, m2 (ft2)
X,Y,Z - body axes system
a (ALPHA)- angle of attack, d eg
(BETA) - angle of sideslip,deg
6f - trailing-edgedeflection,positivewhen trailing edge is down, deg
6L.E. - leading-edgedeflection,positivewhen leading edge is down, deg
Derivatiyes:
CL - @CL / a_, per deg(_
C_B - @C_ / _B, per deg
iii
8/12/2019 ersen nyilazott szrny orrsegszrnnyal val aerodinamikaihatsa
6/70
8/12/2019 ersen nyilazott szrny orrsegszrnnyal val aerodinamikaihatsa
7/70
Introduction
The NationalAeronauticsand Space Administrationis currently investigat-
ing the aerodynamiccharacteristicsof advancedaircraftconceptswhich are
capable of cruising efficentlyat supersonicspeeds. The conceptualdesigns are
representativeof future generationcommercialand militaryvehicles and incor-
porate wing sweepson the order of 70 to 80 (e.a.,Refs. 1 and 2). Unfortu-
nately such configurationshave typicallyexhibiteddeficient subsonicaerody-
namic characteristics. These deficiencieshave been attributedto the formation
of leading-edgevorticies. Numerous leading-edgedevices and conceptshave been
consideredto eliminate or minimizethis vortex formation (see, for example,
Refs. 3 through 5). The present wing geometrydiffers slightlyfrom the geome-
try consideredin References3 through 5. The leading-edgebeing modified to
obtain a constant inboard leading-edgesweep of 73.05.
The present study was specificallyintendedto providea direct comparison
of severalleading-edgedevices. The tests were conducted in tileTexas A & H
University7-by-lO ft Wind Tunnel over an angle of attack range from about -6
to 16 for sideslipangles of 0,- 5 and -10 and at Reynolds numbers (basedon
the wing mean aerodynamicchord) from 4.1 x 106 to 5.3 x 106.
8/12/2019 ersen nyilazott szrny orrsegszrnnyal val aerodinamikaihatsa
8/70
2
Model
The principal dimensional characteristics of the model used in the present
investigation are listed in Table I and shown in Figures 2 and 3. A sketch of
the model and mounting arrangement in the Texas A & M University 7-by lO-footwind tunnel is shown in Figure 4.
The model incorporated three different leading-edge systems and a trailing-
edge flap system as shown in Figure 3. The model did not incorporate either
nacelles or an aft fuselage.
Tests and Correction
The tests were conducted in the Texas A & M University 7-by lO-foot low
speed wind tunnel. The model was mounted in a wings vertical attitude so that
the wind tunnel turntable could be used to obtain a -6 to 16 angle of attack
range (see Fig. 4). A variable knuckle was used to provide side slip angles of
0, -5 and -i0 . Forces and moments were measured with a standard six-
component strain-gage balance mounted internal to the model. Flow visualization
was accomplished using 0.048cm (0.019 in.) diameter nylon tufts. Test were
conducted at dynamic pressures of 3064.3, 4069.8, and 5123.16 Pa (64, 85, and
107 Ibf /ft 2) these values of dynamic pressure resulted in Reynolds numbers
(based on the wing mean aerodynamic chord) of 4.1 x 106, 4.8 x 106, and 5.4 x
106. The majority of the tests were run at the lower dynamic pressure which
resulted in a Mach number of 0.21.
Jet boundary corrections to the angle of attack and drag were applied in
accordance with Reference 6. Blockage corrections were applied to the data bythe method of Reference 7. Balance chamber pressure and model base pressure
were measured and the drag measurements were adjusted to correspond to
8/12/2019 ersen nyilazott szrny orrsegszrnnyal val aerodinamikaihatsa
9/70
3
conditionsof free-streamstatic pressureacting over the base of the model. An
angle-of-attackcorrectionof 0.8 was applied based on comparisonsof previous
tests of similar configurations(Refs.3 through 5).
Presentationof Results
A data supplementcontaininga run scheduleand tabular listing of data is
provided in AppendixA. The results and discussionare presentedin accordance
with the followingoutline:
LongitudinalAerodynamicCharacteristics
Effect of Reynoldsnumber
Effect of leading-edgevorticies
Effect of simpleleading-edgedeflection
Effect of leading-edgeslat
Effect of variablechord leading-edge
Comparisonof leading-edgedevices
Effect of trailing-edgeflap deflection
Lateral-Directional AerodynamicCharacteritics
Effectivedihedralderivative
In additionto the standardlongitudinalaerodynamiccoefficients Cm,
CL, and CD and the lift-dragratio (L / D); the leading-edgesuction
parameter(S) is also presentedas a figure of merit. The leading-edgesuction
parameteris fully discussedin References4 and5 and is defined as :
CD - [ + CL tan [CL /C L )]S = CDsym a
CL2 _ -C k tan (CL /Ck ]
Where CDsym is the drag coefficient of the confi guration without twist and
camber, at zero lift. (See ref. 4 for a discussion of CDsym). The value of
8/12/2019 ersen nyilazott szrny orrsegszrnnyal val aerodinamikaihatsa
10/70
CD has been estimated for the present model tests using the relationshipsym
CL2CDrain
CDsym= CDmin - _A
Evaluation of this relationship yields CD:y_ = 0.0107. The value of CLhas been determined experimentally (from the linear region of CL versus _)
to be 0.039.
Results and Discussion
The present study was specifically intended to provide a direct comparison
for the effect of several leading-edge devices on the aerodynamic performance of
highly swept wings. The model did not incorporate either nacelles or an aft
fuselage.
Longitudenal Aerodynamic Characteristics
Effect of Reynolds Number.- Figure 5 presents the longitudinal aerodynamic
characteristics for the configuration with undeflected leading-edges over a
range of Reynolds numbers of 4.1 x i0 G to 5.3 x 106. As can be seen, for the
configuration with undeflected leading-e dges, increasing the Reynolds number
from 4.1 x 106 to 4.8 x 106 results in only slight chan ges in Cm, CL, and CD.
However, the nature of the changes in CL and CD are such that significant
increases in leading-edge suction and lift-drag ratio occur with increasing
Reynolds number. Further increasing the Reynolds number to 5.3 x 106 yields
no further changes in the aerodynamic characteristics. Reynolds number sensi-tivity studies were also conducted for a number of deflected leading-edge
configurations. These data are not presented, but are contained in the
tabulated data of this report. Results of these studies all showed that with
deflected leading edges, no Reynolds number effects existed.
8/12/2019 ersen nyilazott szrny orrsegszrnnyal val aerodinamikaihatsa
11/70
5
Effectof leading-edgevorticies.-References3 through 5 have shown that
this class of highly swept-wingconfigurationexhibits vortex separationon the
outboardwing panel for angles of attack of approximately2 and that wing apex
vorticiesbecome evident for _ > 4. Flow visualization,using mini-tufts,
verifiedthis phenomenonfor the present configurationwith undeflectedleading
edges. Unfortunately,the photographicquality of this particularsequencewas
quite poor and tuft photographsare not available.
The data of Figure 5 illustratesthe effect that such vorticies have on the
longitudinalaerodynamiccharacteristicsof the configuration. As can be seen
for a = 4, a pronounced non-linearityin CL and Cm versus a exists.
These results are consistentwith previous studies,the non-linearityin CL
being termed vortex-liftand the non-linearityin Cm being termed pitch-up.
Effect of simple leading-edgedeflection.-Reference 3 has shown that a
simple leading-edgedeflectionof 30 is an effectivemeans to forestall leading
edge vortex separationfor a similar,highly-sweptarrow-wingconfiguration.
For the present configurationfigure 6(a-d) shows the effect of simply deflect-
ing the leading-edgeabout the hinge-lineshown in Figure 3(a), for conditions
with the outboard verticalf ins on and off, and 6f = 0 and 20. In as much
as the higher RN data was obtained for the configurationwith aLE = 0,
only for conditonswith tileoutboardverticalfins on, plots of S and L / D
are presented for the configurationwith aLE = 0, only for conditionswith
the vertical fins on. However,noting that Cm, CL, and CD are only slightly
influencedby RN , these data are presentedfor the configurationwith aLE =
0 for conditionswith verticalfins on and off. Comparisonof the data of
figure 6a with that of figure 6b, and comparisionof the data of figure 6c with
that of figure 6d indicatesthat the outboardvertical fins may provide a slight
reduction in the pitch-uptendancyat higher angles of attack.
8/12/2019 ersen nyilazott szrny orrsegszrnnyal val aerodinamikaihatsa
12/70
6
Most importantly, the data of Figure 6 shows that deflecting the leading
edge through either 30 or 40 is effective in delaying the angle-of-attack at
which pitch-up occurs to _ > 8, and that the vortex lift increment is
virtually eliminated. The data further show that for the range of lift coeffi-
cients of interest (i.e., 0.3 _ CL _ 0.6), aLE = 30 provides better
performance than aLE = 40-
Tuft photographs for the configuration with aLE = 30 are presented in
Figure 7. As can be seen for a > 8 some vortex separation is apparent for the
inboard wing panel, while the outboard wing panel experiences plain separation.
This condition, as expected, worsens with increasing angles-of-attack.
Effect of leading-edge-slat.- The leading-edge slat tested, was designed
using simple sweep theory in conjunction with two-dimensional methods. The slat
design was intended to limit the normally high leading-edge suction peaks, to
values for which it was considered that attached flow could be maintained. This
resulted in an average value of slat gap of approximately 0.170 cm (0.067
inches) and an average value of slat overlap of approximately 0.079 cm (0.031
inches). Results for the configuration with the leading edge slat (see Fig.3(b) for geometric details of the slat) are presented in Figure 8(a-c). The
data show that for af = 0 the leading-edge slat is effective in postponing
the occurence of pitch-up to _ : 12 (corresponding to CL : 0.55), and that
with _f = 20 pitch-up could also be delayed to CL _ 0.55. Tuft
photographs for the configuration with the leading-edge slat are presented in
Figure 9. Comparison with the tuft photographs for the configuration with the
simple aLE = 30, shows that the slat tends to suppress the inboard vortex
separation to higher _'s, but the flow over the outboard panel is essentially
the same and is experiencing separation for _ > 8.
8/12/2019 ersen nyilazott szrny orrsegszrnnyal val aerodinamikaihatsa
13/70
8/12/2019 ersen nyilazott szrny orrsegszrnnyal val aerodinamikaihatsa
14/70
8
deflection)it also results in a significantperformancedegradationrelativeto
the 20 deflection,at lower lift coefficients.
Tuft photographsfor the configurationwith the variablechord leading-edge
are presented in Figure 13. As can be seen for either the 20 or the 40
deflection,vortex separationis apparentfor _ > 4. These results are consis-
tent with the force and moment data shown in Figure 12.
Comparisonof leading-edgedevices.-Figure 14 presentsa comparisonof the
longitudinalaerodynamiccharacteristicsfor the leading-edgeconfigurations
considered. As can be seen, the simply deflectedleading-edgewith aLE =
30, and the leading-edgeslat provide improvementsin longitudinalstability
and performancewhich are similar,however,the leading-edgeslat generally
exhibits slightlybetter aerodynamiccharacteristics. Both of these geometries
exhibit substantialimprovementsrelativeto the undeflectedleading edge and
the variablechord leading-edgeconcept.
Effect of trailing-edgeflap deflection.-Figure 15 shows the effect of
trailing-edgeflap deflectionfor the configurationswiththe simply deflected
leading edge and the leading-edgeslat. As can be been, the trailing-edgeflap
effectivenessis essentiallythe same for both configurationsand remains rela-
tively constant for the range of conditionsinvestigated.
Lateral-Directional AerodynamicCharacterictics.
As noted previously,the present model was comprised of a wing-fuselageand
was intended to addressgeneric problemsassociatedwith highly swept wings.
Reference 5 indicates that one of the major deficiencesof this class of highly
swept wings is the excessivelyhigh levels of effective dihedral.
8/12/2019 ersen nyilazott szrny orrsegszrnnyal val aerodinamikaihatsa
15/70
9
Effective dihedralderivative.-Figure 16 presentsthe variationof C_B
with a and with CL for severalo f the leading-edgeconfigurations
investigated. As can be seen, deflectingthe leading edge has the positive
effect of reducingC_B. This result is thought to be due to the deflected
leadingedgeeffectivelyrepresentingsome geometricanhedral.
Summary of Results
An investigationwas conductedto provide a direct comparisonof the effect
of several leading-edgedevices on the aerodynamicperformanceof a highly swept
wing configuration. The results may be summarizedas follows:
1. For the configurationwith undeflectedleading-edges,vortex
separationfirst occurs on the outboardwing panel for angles of
attack of approximately2 , and wing apex vortices become
apparent for _ > 4 .
2. Occurrenceof leading-edgevortex flows may be postponedwith
leading-edgedevices. Of the devices considered,the most prom-
ising were the simple leading edge deflectionof 30 , and the
leading-edgeslat system.
3. The trailing-edgeflap effectivenessis essentiallythe same for
the configurationwith either the simple leading-edgedeflection
of 30 or the leading-edgeslat system.
4. Deflectingthe leading-edgesdownwardin an attempt to postpone
leading-edgevortex flows, has the positiveof effect of reducing
the effectivedihedral.
8/12/2019 ersen nyilazott szrny orrsegszrnnyal val aerodinamikaihatsa
16/70
I0
APPENDIXA
WIND-TUNNELTEST SCHEDULENDDATA TABULATION
As an aid to the reader, the appendix provides the wind-tunnel test schedule and
tabulated longitudinal aerodynamic data.
TABLE AI. - TESTPROGRAM
RUN q,PSF 13,Deg Vertical Fin 6f, Deg Leading Edge
64 0 On 0 Undefl ected5 0 On 0 Undefl ected
107 0 On 0 Undefl ected4 0 Off 0 Undefl ected6 107 0 On 20 Undeflected
64 0 On 20 Undefl ected4 0 Off 20 Undefl ected
9 64 -5 Off 20 Undefl ectedi0 64 -I0 Off 20 Undefl ectedIi 64 0 Off 20 Slat, IA12 107 0 Off 20 Slat, IA13 64 0 On 20 S|at, IA14 107 0 On 20 Slat, IA15 64 0 On 0 Slat, IA16 64 0 Off 0 Slat, IA17 64 -5 Off 0 Slat, IA18 64 -10 Off 0 Slat, IA19 64 0 Off 0 Slat, IIA20 64 0 On 0 Slat, IIA21 64 0 On 0 Slat, IIA22 64 0 Off 0 Slat, IIA23 64 0 Off 0 Slat, IA
Taped Intersegment24 64 0 On 0 Slat, IA
Taped Intersegment25 64 0 Off 0 Simple, 3026 64 0 On 0 Simple, 3027 64 O On 20 Simple, 3028 64 0 Off 20 Simple, 3029 64 -5 Off O Simple, 3030 64 -10 Off 0 Simple, 3031 64 0 Off 0 Simple,4032 64 0 On 0 Simple, 4033 64 0 On 20 Simple, 4034 64 0 Off 20 Simple, 4035 '64 -5 Off 0 Simple, 4036 64 -10 Off 0 Simple, 40
8/12/2019 ersen nyilazott szrny orrsegszrnnyal val aerodinamikaihatsa
17/70
11
TABLEAI. - TESTPROGRAM(Concluded)
- RUN q ,PSF 13,Deg V e r t i c al Fin 6f, Deg Leading Edge,,'.. _ . . J,. , ,.
37 64 0 Off 0 VariableChord, 20 38 64 0 On 0 VariableChord, 20 39 64 0 On 20 VariableChord, 20
40 64 0 Off 20 VariableChord, 20 41 64 -5 Off 20 VariableChord, 20 42 64 -10 Off 20 VariableChord, 20 43 64 0 Off 20 VariableChord, 40 44 64 0 On 20 Varia]beChord, 40 45 64 : 0 On 20 VariableChord, 40 46 64 0 Off 20 VariableChord, 40 47 64 -5 Off 0 VariableChord, 40 48 64 -lO Off 0 Variable Chord, 40 49 64 0 Off 0 Slat, IB50 64 0 Off 0 Slat, IB51 64 0 On 0 Slat, IB52 64 0 On 0 S l at, IB
Out 'BD Gap Sealed53 107 0 On 0 Slat, IB54 64 0 On 10 Slat, ,IB55 64 0 On 20 Slat, IB56 64 0 On 10 Simple, 30 57 64 0 On 0 Simple, 30 58 64 0 On 0 Simple, 30 59 64 0 On 0 Simpl e, 30
8/12/2019 ersen nyilazott szrny orrsegszrnnyal val aerodinamikaihatsa
18/70
TABLEAll. - TABULATEDATA 12
mt,k 2
_ I. I'1'-# n t T_ (-1 -_ CP Cp_, CYP C _F
. 1." .Oe . l?=:p .01_ .0175 .non5 -.ooo p .nOn3-_,b P ,bO -, I _ 7- . ,Np n P -,O02 P ,O Oq7 -, O 0 0 Z ,000 _
-3.t3 .CO - .0411 .0175 .o051 .Oon7 -.O00p .O00_-I.13 .00 . r.(,22 .nlIn .012_ .Ono5 -.ONO P .0004
1.13 .UP . I; '=F .(_14 7 .O17q .no04 - .OU03 .000 33 . 4 o , UC ._IF4 .OPFO ,02 3 ( ; ,.000 6 -, O00 p ,nO0 ]3.r9 .t.O . 3pn4 .0.SA .036(. .0001 -.0004 O00l7 ,9 7 , tO ,46 ;; , 0 7 _ ,n4_9 -,O00 l -,oDor, , o oo 3
10.31 ,UC .5_P_ .1165 ,06F. 9 ,O .qN O -.nOlo .ooo3I_,', F GO , _ 7 57 , l _ q b .OS4 q ,OnO 9 -,O O3 P . -,,_O?n14 , ',_ -, (;1 ._q? ] ,P3Iq .I_PI ,Onl l -.005" -.OOe3
1.15 .O c .13_f .014 = .(;1P5 .O n05 -. no03 .OO0_
AL PF_ cE TA fl. FP CF C_J Cy_ CSF
I,]_ , U_ , 1 2 aP , 0143 ,0 1 7 _ , _005 - ,0 004 -,O OOl-_ , _ ,On - ,1 3_ I , OPo P -, NO2 a ,On o 5 -,nO0 3 , n o 0_-3,1 7 ,UO -.03_ .O1P_ .n OSO .n on7 -.ooo 3 .hOO p-l,n q - (_0 .0_7_ .nln7 ,O _ P .Oon5 -.nO03 ,oOq O
],I F , 00 , 13 _4 . 01 4 3 , 0 17 P , Oon3 -,o00a , oO n n3,_P , 00 ,_FP4 . fl 2 _ 7 ,02 2 7. ,o q n_ -,0 00 3 , nOnO5,_'A ,uO , 3 4 2 _ ,o&41 .034_ -eOl IN_ 1,0 006 ,000_R, I P .Ue , 4 F1 7 07P4 , O5_F -, On0 3 - , 0 00 7 -,no04
l o, _ P .oO ,_ P 47 . i ppg , 07 3q ,Go00 - , 001 5 -,nooq1_. q_ -,1)2 .TNFq .177_ .102_ .On lO -.n04_ - ,O0_ i]_._h . .04 .r_;f .Pg_2 .1 _6_ .On pO -.O08 P -.O13F1P, nI -.r_: l,_ )P6q .36 n4 ,1571 ,of)q6 -.011 3 -,0176
1. 7 _ .On . 1 44_ . N] 4_ , o l Tq ,On02 - .000 4 . O00S
_l,k 4
ALF_A _TA CL CP C_ Cn i_ CYP C _F
].P= .00 .141= o]4q ,0176 .Onn4 - .OO0 5 ,OOO3- 5._ 7 , UO -,1 3 F= ,(.PN4 -.0033 . Oon4 , ,non_ .0oo7-3,34 -I 'O -.03F : ,_]Pl ,OOSp ,On o5 ,0003 ,OOCA-I.OF .UN .N S]2 ,l' loq ,01_7 ,OnnF .00114 ,_004
I,E_ ,On , 12PP . oI4P .0173 0 003 -,000 _ ,noo43._ ? ,DO . _400 . n p_ 3 ,0 2 3 5 , OOn4 - . 0004 ,oooq_.00 ,O0 ._rr_. .,_ ,n4 o o ,036? - _OO4 - ,n O07 00065, 4 ? .on .4m 3F ,0_4 ,055_ :bnn3 -.o009 .00_ 7
]O, U6 ,U o ,_ ] I , = ,1 3? _ , OP 03 : Onn_ -, O0_ P -,On0 3,_8 , I , O . 1 4_,_ , Ol4q ._ITP 0,In 3 -, n O0_ , 000_
,_k P F..A _E I '_ CI. ('F) f.F' C_t_ 'v k C_F
1,17 ,GO ,1417 .nJ a4 ,0181 .OnnF -,{ _001 - ,,no0=-__.5 2 .on -.1 71_ ,O lql -.o011 ,COn8 ,O00(i - ,OO Op-3.P.a -{_0 - .(i?6q .011 5 . t_067 .00o7 -.O00 l -.qO0 _.-l.lt; .00 . n.r-(_0 .nln3 .013r5 , { , nne .o00n - .noo4
l,J F ,0 0 l 3 q.'? n l -3 ,Ol Vl , On n_ - , _nO ] - , nO N= .3 ,44 . 00 F37_ , n P_ . ? , OF. E_- , Onn7 - ,OU 0 3 -,oo0 15 . 7_ , uo .34_ ._. . o_._p ,n 3 9_ ,On n ? -,o00_ -,oo o p7,qc , GC .4zf7. , 0 7o_ ,061F ,Ono_ -,_100 3 -,(_00_
10. 31 .ON .S_6 ; .1 P| 1 .oP_] Oi_n_. -. OOOla -,_O O] 4 ;.F,' , -,Ol .f-70_ . 173_ ,liFO .0o 1 6 -,003 _, -,O04 e.14.q7 -'('Z ,7q=3 ._'3 Qq .] 463 ,0031 -.0070 - .O0_'n
1,1F .Uo ,i_ .31 .0144 ,0 l F_(. .0q{16 -,O00l -, 000_ a
8/12/2019 ersen nyilazott szrny orrsegszrnnyal val aerodinamikaihatsa
19/70
TABLEAII. - CONTINUED 13
_t. F, e .
ALnt -b n I , _ CL ( D CI4 C o t , , _ ( Y P CcF
-_ .09 .00 .03_ 'q .n? 4 *.P243 .00_)5 -.0{_03 - .nO0 ?-27 .00 ,1 204 .r)pq 4 -.0_42 ,oon4 -.0003 -.000 2
-._ . Un .;0_7 .(_? _ -.niP5 .non5 -.{boO4 -.on03I .e l .uO .pc:;. / .,_3_ . _. -.01 54 .oon; _ -.nuo 5 -.nO0 34.IP .00 .4 0_q .OC_f'; -.OOP l .UonO - ,0003 -.000 2
,5 _, .uO ,_;' _ ,h_n4 .O0_.q -,0004 - ,0007 -,0007c ,. (1f. *00 . _._,_, '- . I _':.? , O_._E6 -.O lin5 -.(IUU7 .0003
11.51 ,O0 ,7q _cz . 1n31 r)-r'O -,Onnl -,0024 -. 000 =12,90 -*1:3 ._ FP .2_.7q ,0867 .Olin7 -.O05P -.O07 Q
I ,_J z, ,nO .30nF . n .'zT._ -,olEI ,00o -.000 '_ ,n Oel
Pt: h 7
ALPI -A pET_ CL CP CV C_ M CyV CF F
I._;F .CO .2 _72 .n_6 -.0147 .Oon3 - .o00 _ .0000-_.ll .uO .0_5 .n? n_ -.03 _3 .oon7 -.000 ? .00C1-_._P .o0 -1 _3 .o_ pn -.n _2T .Otln_ -.nOO P - .0_01
-,_9 ,Oq ,gn_ ,0?_6 -.017 F ,O()ob -.000 2 -.0002],SF ,OU . 2_7P .03_4 -,Ol4q ,Oon _ -,OOU _ -.ooo]3.P7 ._10 .400_ .q_q -.O0_O .O _nO -,000_ - ,0003_,]e *00 .EIIO .0234 ,0073 -.00_? -,00 0_ -,0003P .4_ .UO .6_6 , 1? _q ,0 _23 -,00n3 -,O00h .00 0]
l_._, .uO .7 _]? . 17, _ .041 _ -.oon3 -.nol_ -.0 00_13,1g .,0 , _79 .P 3_ .0694 ,On _ -._04& -,003_l_.4P -,01 ,g? ?_ .30 70 ,lOB? -*Ooa& -.0063 -.00_17,75 .,02 1 ,0_7 .? _ ,15 32 -,O_3F -, _08_ -,00_|
1,59 ,UO ,301= ,n_7 -,014_ ,0002 -.0003 -.00 02
gU_ P
ALP FA pET A CL r P C_ Cn_, CYV CS F
1.52 .O O ._qPp .02_4 - .014_ .0()04 - .O00P -.nO0_-_. lO ._O .0_ 30 . n2o 6 -,O323 .00n7 - .o001 -.o0 o3-_._ 8 .00 .1 2_3 .o]oP -.0_27 .On o_ - .000 1 -.o0 0?
-,hp .O0 ,_070 ,n?62 -,0177 ,Onl )7 ,OOO n -,00071.59 *00 ._q_7 ._?R _ -.0148 .001 _3 -.000 _ -.06 _3.gl . 00 ._07F .P _6_ - .0059 .Oonl -.00 02 - .00046.]q ._0 ,_140 .n _O .o10 _ .oo0o . -.0002 -.OOn __._P .00 ._42 .17_ _ .O_q5 .00 00 -.0003 -.0003
lO.P3 .O0 .74 _3 .17qq .0 504 .O on -.OOI)9 -.001_13 ._1 .,01 ,F7 _7 ._a _ .02 _7 ,on13 -.OO3R -,00 _3]E,SE -*02 l,O06P .._7_1 ,1095 *0030 -._0_7 -._7_17,qO -.03 1,1 2_7 .414_ . 14q q .Onn7 - .n07 _ -,_ ;0
l.hl ,o0 ,30_ 7 .0_7 -,0146 ,oon3 -,ooo p -,0007
_U h e
ALPPA pET_ CL CP C_ CgM CYW CFF
]*_l =.Ul .30_ .O_n -.OIE? .Oq _4 .004 2 -.0227-E.O 9 _.01 .0_72 .O? ]F -.033 P .O_nF .n047 .00 _3-_,RF _.0 1 .|_ F? ._2n p -,0_3_ ,00 _3 ,Ofi4 P -,O0_P
-._7 :*(' . _OP = .Op=_ -.0123 .00 ,5 .0039 -. 01_I.SC _,01 .3o1 . o3_P -.012_ .oob_ ,O0_l -,022__.q _ _ ,eo .40 _ = .0_ -.O0_P .O Oql .1J04 3 -.0347(.lq F*(: O ._I_F ._h7 .013[ .OIIU ,_03_ -.O_
I0. _ _ ._q .7_? .1 _1_ .O_B? ,014 _ -.000 _ -._7_;
1_._1 6-_7 I.OIP; .3 7_ = .117 1 ,01 _7 -.quT _ -.lu3?|5.q& 4._ T 1.1&_ ._q%P .I _ .01_ ._ -,v1093 -,IIPO
8/12/2019 ersen nyilazott szrny orrsegszrnnyal val aerodinamikaihatsa
20/70
TABLEAll. - CONTINUED 14PU_ 10
ALPP F pETA [ f_ CM Cn_ CYM CS F
I,F? 10.0P .3141 ,O_F -.OOZ3 .0130 .OIO N -,n 4A_-_.0_ i0.04 .04_ .n p46 -.o330 -.0_) il .o111 .ooR3-2._ In.U 3 ol31q .077_ -.o21o .0t_37 .OOgq - .OO eB
-o@6 0.03 ._lqE .OP? G -.0114 .Oo R6 . 009 _ -.02 qO
1.62 l;_.O_ . 31_P .03q4 -.0 026 .0130 .O09q -.044_3 .9_ IO.Ul .kiln . n=p_ .OOOP ,0175 .o094 -,06_06.lq I_.0 1 ._14_ .nA 7_ .0_74 .Olqe .OOB3 -.0R77P .51 In. U0 ._3_q .IPe4 .05 07 .0 _31 .0053 -.1107
13.1_ q. _P .F3 73 .P353 .lle7 .O pn2 -.0029 -.lff7115,3_ _ ._e .q3o4 ._0 3P .15_1 .Ol_e - .o053 - .17_o
1._ la.02 .31_ .O_ q5 - .0021 .0135 .aOq 9 -.0_5_
_ Uh 11
ALPF_ n EI A _L Cn _ Cp_ CY P CS F
1.50 .0_ . ? ec S .n_3_ -.0_15 . Ono3 -.0001 . 000_-_.IP .00 .nl4e .,3_ -.0571 . Onn7 -.o003 0 003-2 94 . u p . I _ 4 _ . n 3n7 -.0439 .00o(, -. 000 2 .000_
- . 77 . _0 .1 , _ ._ Q6 - o0 3 _6 .{ ] _ n _ - .O OO_ .O 0 0 q1.5_ -flO ._ 71 .fl?_ -.OZIQ .0_1_) 3 -.0001 .0010
3.7F .OO . 347C .0_1_ -.nl4P .Onol -.ooo3 .OOQ_5.q F . OO . 4 _ 7 _ .l__ _ -. OORl . On n O -. oo 0 _ .OOn7
10.43 .00 ,_ q; .oqo_ ,005_ -.OnO_ -,0013. -,OOl _12._4 -.Ul .eTl_ ,13PO .0 211 -,Onl 3 -,003_ - ,004_16 .H_ --O2 .7_7_ .17_7 .03 45 000003 -00055 -0010717.1_ --1}_ ._4_ ._?01 .0514 -.On_l -,_0_0 -, 007_
l.bO . bo .?e_ .07_4 -.oP l_ .Cq 03 -.OOOl .O01q
PUb 17
ALP_ pLT4 CL 0 CM Cgu CY_ CSF
1. _p .OG . _7P ._3 -.0223 . 0_(_ -.no0_ -.OCO_-5,_4 ,Off -.0 00_ ._|_P -.0603 .0003 -,_00? -,000_-_o91 . DO .Oq _ .n31_ -.0460 .OA_)4 -.nO_ -.O00P
1._7 .00 ._7F .q _q -o0223 oOq l02 -._OG 5 -oO00_3.qq . 00 .2_0c .04 7? .fll _P -.0011 -.flU0 5 -.0010_.Z? .OC .435F .OCEA -.0079 -.O _)fl_ -.OOO_ -.00 11P.SF -'01 .5_ ._7_; -.0013 -.Oonq -.00 05 -.001_
lO.e _q -.0_ ._]P3 .1057 .0077 -.0011 -.O01 P . -.004313.?0 -.04 ._6_ .I_P_ .0_3 -.0010 -._10 44 -.OOqP15.5 G -.u7 .7 _ .1_3a . 0414 -.Onl _ -.n07 o -.nlel
_0. 37 ..07 I._P _c .3_q .oel _ -.0n 72 -. oo lp -.nlpp .7 _ .00 ,_05 .n ? _7 -.O_ CH ,O On3 -.000_ -._ CO7
Rt:t. 13
ALP t.'. _ PI'.' TA CL _n _ CP t_ CYP CFF
I ,r' -? .O 0 ,_7_ .1_4 I -. 0;_0_ .Ono O -,hO OP .onoP-5.IP .00 ,OI F7 .n37n -. o5 (:(_ ,{'onb -.OUO_ -.Oe nl-2 .9? .uo .lOPe .n _n_ - -.n43o .oon5 -.n OO3 -.o ool
-.74 .on . l ':;o: .n3 o] -.0317 .oqoP -.00o'_ .nool1.4,_ .00 ,;.70(; .n _?7 -.020R . UO00 -._)003 ,oOn33.7_ .t' O .34 _(; .o_ .1 p -.n13 4 -.Onnl - .0oo4 -.O 0Ol5.q3 . _0 ._pC_l .nc43 -.0074 -.t_on3 -. POO h -.no038.1 _ .U(, .=1_,c .07_ -.0015 -.UoI , q - .nO07 -.00 13
10 .3_ -. 1}1 .e._31 .Oq a5 .0_3_. -.Oooq -.0013 -.0C331_ .5CY -.I ) I .ef.O_ .IPQI .004_ .Ooql .00_7 -. O0( -'-14.7 n ..03 .TlPC_ . _ .7 . n(_F ._. - .Onil -.oO Tp -.h i3 ]15.r_? -.1 :3 .7 _.h l .;I _7 .O&_7 -.Ut_ 34 -.nlO() -.013119. _C ..o,_ .F_5 7 .pP n_ .OEIR -. Oor_P . -.0075 -. 0077
I .4_ .oo . _-eR 7 . {,337 -.n _oe .Onn ? -.00 0;_ .non=
8/12/2019 ersen nyilazott szrny orrsegszrnnyal val aerodinamikaihatsa
21/70
TABLEAll.- CONTINUED 15 I_ l . t, 14
ALPP_ ptl^ CL C9 C _ C_u CYP CSF
|,bP , O0 o_7_ ._4_ -o 02GP oOo03 -.000 _ -,OOn7..1_ . uO . nO_q .O_P C -.05R_ .O on4 - .0003 .000 2.2._q .CO .leO0 . _1_ -.04_0 .On n4 -. 0003 -.O00_
*.E_ .UO .laT I .rt_N_ -.032 _ oOo N3 -.0005 -.000 41._5 . UC o 27C .0 _47 . -.o21 .O,o| -.0005 - .0002
6,2 _ ,OO ,{_c? .N_? - .O0 6_ -.OLIN3 -,OO OF -.NOe
P .5_ *o01 .5 _1_ .077 _ -,0003 -oO ONA -,1 )007 -.OOl _lOoP7 .o O_ ,e _4 . 1o_4 , OO_8 -.01)14 -,fl O|_ -oflOk613,0 _ . .04 .b _2 .1 _77 0335 -.no? ? - .0037 -.009 _1_.30 -.u , o7 __ olO ?; . 0541 -,00 _ -.o Oe_ 3 -.Ol *n
20. |_ - .|C ._731 . _?47 .O P gP -.u n_O -.n u33 ..n?_1.70 .OO .;767 .,)7_ -..:203 .Oon l -.OOOfl -.O00_
ALPHA _TZ (L C_ Cu C _N CY_ C_F
|._p ,OO . _17 . _177 .CO _] .0_1_ -.O00 p -.0002- 5,_ E .( I0 . , l ap _ ,o _ nl *,0 26_ ,on nP -.qOO _ - , _ n0 7-2.3_ .,_ -.0_1 .n?_? -.0131 .001 0 -._UO_ -.0011-|.15 .UG ,0_0_ .NIP_ -.0020 ,OnnP - .onn _ -.no0_
I.I; .O o .1E97 .oI PO .oOPO . (,,I0_ - .0003 -.00023.37 .O 0 ._I_ .NP I? .015_ .Onnk -.0003 -.O00F_._ .oo ._ql_ .07_I .022? .Oonl -.oOO _ - .OOll7.75 .00 ._ 741 .O _l_ .OPt7 .O noO -.0007 -.G_I_
lO.On ..Ol , _{'0 .O _nq ._34B -.o nn_ -.ool_ -._o3q12.?E ..u _ ._4(.7 .oaTh .O _lq -.OnnP -.0029 -.no _14.4_ ..03 .@1,1,7 .1177 .0_43 -.0.41 -.oo5. -.011_16 .53 .,O_ .e _P_ ,1_7 .O _Oq -.0_3_ - ,_OP1 . -._107_.R2 ..0_ .7_P O .21_0 .1094 -._U_ -,oUP _ -,O07p
l.lO ,UO .1313 .017_ ._UB_ .00o5 -.0007 -.O00E
_b h 16
ALPHA p kIA CL _n (_ Cop, CYF CSF
1.10 .GO .1304 ._lTO .O07 q ,.ONn 5 ,QoOn -,00 _--_._l .00 -.]47g .0_77 -.0?_ ? .OnnP -.o00_ -.oOn _-_._I .oO -.14P] .n 37_ -.0_63 .oooP -.ou o_ - .o _0_-3.37 .o 0 -.0532 . _? _7 -o0130 .OotO -,O003 -.O Oln-1.1 3 .00 .0 _24 .Ol P= -.0017 .ONo P -.00 0_ - .O00 q
1.0 _ .00 .127 _ .P174 .0077 . O_n_ -.0_01 -. OO0_3.3_ .00 .2120 .oPn2 .0157 .Oo o_ -.0001 -.000__.57 .O0 .EgEO .07_0 .021_ .Oonl -.000 3 -.O01 07,7 _ .00 , 372_ .0_ _ .h2 fl| .O,) o_ -.000 5 -.001_
I0.01 ..01 .4_00 .O_O0 .0357 -.0111 13 -.0015 -.003012. _ ..02 .$4 _7 .0 P77 .O _4g -.On)6 -.nO30 -.00 _714,43 ..03 .blgO .IP ? _ .0629 -.0005 -.004 _ -.011_|6.67 .*02 .700 _ .IFPfl ,OR2O -.0044 -.OU PP -,ooq _18,9 3 -,01 ,7 _73 .? _7_ .I017 -.00 _0 -._090 -.005 _
1.1 _ ,uO .l_e .o173 .OOe _ .Ono _ .ooo _ -._oo_
ALP PA _ET_ CL CE CV Cp _ CY_ CSF
1.1 , _.0_ .123. .olO* .006o .0 0_3 .OOe2 .OOt _-_.bO . O_ -.143 _ ._07 -o 02_3 -.003 _ .olO R ,03_P-3.3_ F.04 -.0,74 .n?Tl -.0135 - .On07 .olO .n ?_-1.13 _.03 .0,6_ .o;n _ - .O02P .On n7 ._oq_ ,_1_1
1.1_ =.03 .131 _ ._I q4 .O0 _b .O, _P 2 .NO_2 .OOl _3.37 _.03 .7143 on e? _ .014 _ .ori e l .no7 0 *.oOE3
7,7 P _.0_ .375_ .{_42[' .0300 .0_I_ Q .n073 -.0177]O.C J _ .b3 ._t.7_ .liA3 q .N3P g .00_5 .OOe_ - .N_ 7I_._e =. 00 .E4FE .n _13 .()540 .OI J _ ._0 7_ -.0,_?14.4 _ _ ._p .F 2_ .177 n . _7_q .Ol _ .00 _7 -,O _2P16.73 4.qp .71P c .17#_ .0E95 .Oli6 .no_ -.07 _
lq. O0 _ .q _ ._l_n .;_P .107 7 .N,71 .nO_ -.OTRQ
8/12/2019 ersen nyilazott szrny orrsegszrnnyal val aerodinamikaihatsa
22/70
TABLEAll. - CONTINUED 16
_LPh _ BETA CL C_ CP C_, CYP C_F
l , Ip I0.07 , 13P4 . nps P . 007 3 . 00 36 , e l * 6 , 0 05 7- 5, ,7 I 0 o 10 - ,1 3 1q . 04 7 1 - o 02 74 -,O0 7 P , 0 23 6 , 06 _S-3.3_ In , u P -.03 3 1 .033 5 - , 0146 -oO Opq ,0 2 1& , 0 431- I . l ] iO.C7 .05 6 F .O P_P - . O0 3P -oOnn] 019P . OPlq
I.I 0 I0,07 . 12 _ , OP4 R .007 7 ,0035 ,01 8 4 , OOffq3, 3n I 0 . C7 . _PO ,O p n 7 . 0 1 8 0 ,0 o7 5 , 0 17 8 -. OOP__,6_ le ,07 .3063 .n 777 .0 283 .01 16 ,h iE? -.024n7,P3 lr.O_ .2q7& .0_33 .039 7 .Ol_l .0706 -,04 _&
I 0.08 1 0.0 _ .4 8 5 6 . 07 3 _ .0 54 7 .02 pI . 0201 - , 076 q] 2 .3F IO,OI ._776 .I 05 F . 072 0 .0 _ 3 _ ._18q -.Oq q O1 4.57 In . O0 , 66 4 P . 1 44 p .08 8 9 .O p05 .of 7& -. I I _ 3I _ . _4 I0,00 .7 _1 2 .IO F O , l l Ol .OI R6 .o le6 -. 1 37 619 . 11 _ . qP . P _93 .p_ 4 .13 5 1 .013 7 . 01 53 -.1 6P ?
l,lE 10 .06 ,137P ,oP_ . 0075 .0o3 6 o018 4 o00 3
rt.h l_
_LPP A v[T# (L Cr C _ Cp M CYP CFF
l.l ,bo .130 _ ,n]_a ,OOq4 oOnn7 -,ooo p -000 7-_,t_ .00 -,14P C ,n377 -.0250 .O0 0e -,O00 P -.O0 0&
-3.37 . 00 -,u fs_ . 0P47 -.010 8 ,Oo nF -.0OO p -.0004-1.14 .00 .040E .O]oP .O00P .00nq -,0001 -.O00 FI,ll ,00 .i_? .01_7 , OOq4 .Oon7 - .0001 -.00063,37 .UO ,? IO_ .(;? O_ ,0167 ,0 003 -,OO OP -,000 _5.b6 .00 . 2PC _ .027 q .0F35 .Ono P -,0003 -,00 077,7q .00 . _ 7 4_ ,_4 n _ ,030 4 ,O0 0 P - ,OO OP - , 001 _
IO,O P - ,01 .45P_ ,fl606 ,03_ -,00o3 -.OOl_ -,0 037)_,27 -*t)_ ._e_2 ,O POP ,04 q3 -cOOl U -,q03 7 -,008 314,46 -.03 .e Pl; .]PFO , 0680 -, no n& -.OO&9 -.O]Oq1 5 .6_ -, Of ,700_ o 17 10 ,O_ q 4 -,Oo a 5 -,00 55 -, 0 06 7]9.q _ o 0 1 , 7_6_ . p3 p l .I1 34 - .0o n 6 -. n 0 5 3 o00 _ 0
I.IP ,o0 . I731 .o] a o .oO qq oO(|n6 -o00 0? ,000 =
_t_ ;0
^LP_a _L1h CL rp (.p C =t,_ f YV CFF
]l ; ,co .1 3 _ ,q1 7P ,0 0 9 7 .oo n7 -,co n 3 - , 0 0 0 1-5.h i ,{_0 -, ]_h O .O_ 7P -,0Z43 ,Oot)P -.OOOP ,OOO l-3,3_ ,O0 - .O_S C .h?5_ -,0103 ,0o10 -,O00p -,00 0_-1o13 . bO .0_11 oO lP7 ,0010 ,Ono _ -,O00 P -,0oo|
1,14 ,#_0 ,12110 ,n1 74 ,oOq _ ,ooo7 -,o00P ,00003,3_ . 00 ,;oq7 .nP]l ,0171 ,Ono_ -,0003 -,00015.5_ ,1;0 ,_qnG ,opt? ,024 ? ,Gn ,l -,0005 -oOO Oa7.77 * 1 1 0 ,27Fg ,o a ]6 ,030_ , Oo o F -,0OOP -,0011
lO,O l -.01 ._=o ; .0_1 _ ,03FO - ,Ooo_ -,o017 -,00 3_l_.2q -.OE .5_Cl ,nnq_ .o_6 h -.Onoa ' - ,0031 -.OOq31_,43 -,02 .*077 ,l_nl ,0697 - .oo_o -.o037 -,00_616o%P -.o_ ,{f ]_ ,l_f17 ,og P7 -,O0 3P - .0_43 -.O07Plq,P_ ,01 ,7_54 ,PlP7 ,1_06 -.O07P -,0043 ,0037
1,10 , u O . 131_ ,0170 .o o gg ,OO O6 - ,OOU3 ,000%
r Ub ;I
ALP P_ n t7_ CL _ CF ' Co_ CYP C_F
l,l; ,O0 ,130 q ,0170 ,OOg7 ,Onn7 -,0003 -, 0003-5,67 ,00 -,14_ 3 .o_TP - ,0_47 ,Oo lO - ,O00p -,0003-3,3_ ,00 -,05_ ,oF67 -,n llo ,Onll -,0003 -,CO03-1,14 ,uO ,0404 .OJPP ,000 4 ,On]O - ,0003 -,OO04
l,ll .bo ,l_gP ._|70 0096 ,on07 -,000 3 -,O00P3.37 ,00 ,PI07 ,opo7 ,0173 ,on04 - ,O00 & -,00045 .5 7 . CO ._O0 ,O_P_ .0_4 3 ,0003 -,nO0% - .c o n P7.77 ,00 ,775f ,041 0 ,0307 ,O( IoP -,000_ -,0016
10 ,04 - .01 .4_64 ,o_P1 .0361 ,O0oO -,POIF - ,004112,zo -,t)? ,54P_ ,o_o_ .o&_o -.Onl ? -,oo_ q -.OOO314 ,4_ _.OE ,_17E .1P37 ,()7Z3 -.Oop7 -.n037 -,OlO I16 ,FB .,Op ,_q56 .lTP _ ,hqO 4 -.0034 --,O05 A -.007319. 0_ -.Of .P l_6 .TAP_ ,lZFq -.Oo_q -,0037 -,OOE7
1,11 . 00 ,13; P .01_ ,OOgq ,On 06 -,0003 ,0001
8/12/2019 ersen nyilazott szrny orrsegszrnnyal val aerodinamikaihatsa
23/70
TABLEAll. - CONTINUED 17
ALPHA pE TA CL CP C V CpN Y_ CEF
1.1_ .00 .12_0 .ol _P .009 7 .ooo7 -.0 o0 - .no0,-5,63 .00 -.14P 0 .0_ 72 -.0245 .O hiO -,o0o1 -.0_0_-3.39 .O0 -.0F37 .O ? 4Z -.OIOP o Vnl2 -.0 00? -.0007-1.1S .{=0 .0416 .o17 6 . . 000 8 .o onq -.000 ? -.0004
l.ln .00 .12ga .01 63 .oo q5 .oon7 -.0001 -.oO Oa3.3 P .oo .211 _ .o loq .hi70 .oo n3 -.0007 -. 000_5.57 .0 0 ,2PEP . 0774 . 0235 ,0002 - .non & -,oOOQ7.7 q .00 o374P .n_ q o . 0301 o0000 -.00 09 -.OOl_
I0.01 -.01 . 46P 1 .n _nF . 0374 -.O00P - .qol4 -.003112 .27 ..02 ._ 41 4 .nA n 2 . 05 26 -.0 o 0 5 -.no4p -,00 9 314 .51 . .03 .6_ 35 .133 P .066 8 -.0002 -.n0 34 -o011_16 .81 ..OE .7453 .lnqO .0 _ -.O04& -.OOSn -.O0 6F19.1_ .00 .P (_ .p_P 6 .11 21 -.O07 b -.o02 l -.o00 e
1.1_ .00 .]3_ P .el_ .O Oq9 ,_00 7 -.0007 -.0006
_h _ 3
ALPP _ pLT A CI. Cn CV C_ CYV CF
1.15 . o0 .12FF .n lTO .o077 .ono_ - .O00P -.oen_-5,bO .GC -.14P_ .n 373 -.0266 .non _ -.00 o3 - .o00_-3.33 .On -.o&*F oOP, F -.0 131 o0_] -.nO0? -.0001
-1.1_ .0 0 .o4_ 1 .nl_ -.0o21 .nolo -.oooP .noon1.13 .bo .1 _= .n] _ .007_ .Ono_ -.0003 -.000_3.3P .00 .2 11 _ .O;O 1 .0153 .Onn _ -.nOn? -.OOO_5 .5_ .00 ._5 .0775 . 021 7 .On02 -.0003 -.O01n7,8P ,oo , 379g ,0413 .0281 ,0=100 -,0005 -,000_
10,01 ,.01 .4E_O .n=qs .0344 -.OOn P -.00 13 -.0020I2._P .,01 . 53P _ .0_7? .0478 -.00 i5 -.0040 -.005_1_,5 3 .,0_ ,639 4 .1P *_ .OSq P -,onn_ -.0o 5_ -,OOS qI_.7 P 02 .73F_ .IP 2_ .075_ -.0035 -.O06O -.010719 ,10 .,02 ,P&_3 .26c 7 . 0 q 34 - .0067 -.OOb8 -,OOEP
1.15 .00 .13n4 .n]_7 .0083 .On06 -.noo l .000_
ALPP a =E T_ CI C_ CP Cnt. CYP C _F
1.15 .00 ,12qq ._ 1 77 ,0081 ,O o f15 - . 0 003 -.0006-5,5g ,n O -,14_0 ,037 q -,0270 , O_O P - ,000 4 -,000 5-3.3 _ -_0 -.0557 .o ? _g -.0137 .000_ -.0005 -.0007-1.1 4 .00 o03 PI .01_7 -.00 2_ .On o7 -.000 4 -.000 _
1 . 15 ._ 0 . 1_74 , Ql 7q . 007 6 .O on5 -.000 3 -.O00 P '.3.3q . 00 .21 0_ ,n? 13 , 0 156 .Oon_ -.0003 - .00045._0 ,00 .2901 .op*n .0220 .0 001 -o00 04 - .OOlP7.78 .CO .3733 .04]1 .028 4 -,O00l -,0007 -.00]7
10 .0_ - .01 .4_ 3E .n 613 .033 4 -.On06 -.oo l? -.on3 e1 2.2 8 -. 0 2 .F 4_ 7 .O P T_ . 0 43 _ - . On lg -,0033 -.OOP O14,4 5 .,0_ ,6130 ,1206 ,0657 -,003 2 -,0061 -,OO P P26 ,66 . ,0_ . _9 01 . 2_7 3 ,08 go - .On3 _ -. 0 0 7 5 -, OI OF18.9 = ..0 2 .792 R .?? _3 .lOB3 -.0 0S 5 -.0070 -.0077
1.13 .00 ,| PF q .0277 .00 80 .Oon4 -.0003 -.0002
nLh _5
ALPH_ _ETA CL _ CM C_M CY_ CSF
1.I 0 .o0 . l lfiO .nl a l ,o13 q .O o Oq - .00 01 -.0007-5.b6 .00 -.1750 . _377 -.0094 .00 _1 .000 1 -.0007-3.3_ .00 -.ObO0 .0_4_ 0022 .0_14 .oOO l ,0007-I,1_ ,00 ,0_77 ,01 7_ , oO g7 ,DO 10 -,000_ -,00 03
1.11 .o0 .2P1 3 ,014 _ .o13B ._ ,)0 _ -,0002 - . 00 0 33.37 ,00 ._013 .hi ll .02 76 .O on5 -.0003 -.non 55._6 ,O0 .E7 3_ .OP_A .025b .Ooo_ -.000 3 -.00 207.74 .00 _ 4- .n37_ 0347 . Oon5 -.0 003 - 0016
10.02 ..01 .446_ .0_6 .04 21 .O_n7 -.0013 -.003]12,2 _ ..o_ .5_55 . o o17 .0553 . onnc -.0031 -.o08_14, 52 -.03 . _333 .1310 .078P .Ono4 -. oO b3 -.n 12F1_.75 .,03 .7164 . 17 P 6 .flqq 6 -,O0 2l -,0077 -,O13g29 .0_ .00 .P_fi3 ._74 .1225 -.Oo_ P -.n |)SP .oo0_
8/12/2019 ersen nyilazott szrny orrsegszrnnyal val aerodinamikaihatsa
24/70
TABLEAll. - CONTINUED 18
_t_ h _6
AL.PFA pE Ta CL Cn CV CNu CY_ CFF
I.II .o0 ,IPnF .O l4P .0140 . o007 -.O00 P .0000- 5 . 66 . 00 -. 173 q . e 3 al -. 0100 .Oo l l -.OCO l - .0001-_o42 .OO -.oro _ .op4P o0021 .OOl3 .O00 p -.0004- I . I P .o 0 ,0200 .017 7 .0 1 00 0 0 0 8 -. o 00 a -. O00 1
1,13 ,00 ,118P , O14q ,O13q ,oon7 -,0004 -,000]3,36 ,oO ,_03P ,olP2 .0176 o0 005 -,0004 .no0 o5,57 ,OO , ? 7P_ ,0? 60 ,0745 , 00o 2 -,000 4 -,OOCP7,76 ,00 .3613 ,n3_ ,0323 ,0o03 -0006 -,0010
10.04 -.01 .453q .OFoP .060 P .00o 3 -.nO 13 -.00 2_lP, 3Z -,0_ ,F_ ,F ,nqn3 ,0497 ,00o6 -,0033 -,007_14,57 -,O3 , 64Rq ,lppp .0677 ,0002 -,007] -.011 _16 ,P4 -.03 7460 .lTnO .OP4P - ,00?3 -,008_ -,012819,15 - ,01 , 8_3f o?4_q 10 61 -,0060 -,OG k6 -,0 027
r t _ 77
ALPP_ m ETA CL _n C_ Cp u CYP CSF
]. _ F .oo . p 73 4 .0 3 Pl - .OI S P . 00O 4 - . 000 _ .0 00 3- 5 ,_ 0 * u o - . OOgl .o 3n 6 -,041 6 .On Oq - ,o 00p ,000 3-p. 9 7 .00 . OP_ .npoO -.0 3 04 . OL_ o 6 - . o o op ,oo c 3
-.74 .OO ,]TCq .npTF -.NP2g .O No7 - .00 0_ .NO0_1 .5 : .00 ._ 7 01 .n y lq - . OI P A . Oo o_ - .O00_ .nOn__. 7 q ._0 ,3_03 ,Oa l_ -.0134 ,Onq l -,0004 OO O4",qq .O0 .4 317 ,o=a l -.OO P3 -.On(,1 -.000_ . On OpP.l a . o o .=17 P . 0 7Pq oO l _ . o n o] - 00 0 7 -. OOlO
lO,a_ , O0 ,607_ ,OqO5 0076 -Onn 7 -,001_ -, 001 _I_ .7 7 . .02 o 7 1 35 .1 1a n 0195 - . 0 , ) 0 1 -._ 0 _ 3 - . 0 0 711_,q5 -,02 .TPR_ ,IPP O o_0o - ,o015 -,COb l -,o0_17.2P .. 0 7 .P P7 7 .;_77 . 0 60 , -, On ? q -.o071 - n l 3 V1q,51 -,0] . q _l .3Qq7 .0835 -,00_0 -,0037 -,0036
1."4 ,oo ,p7_ u .o3Po .0 1 _5 .OooE -. OOO4 ,ooo_
_Lt'F_ nF1 a CL r _ CP C_ (IY N C_ F
1.53 ,00 .271_ . n 3n c -,OlqO .000_ -.0 0 0 3 -.0004- 5 ._0 ,CO -.OOF 6 ,qT_ -, o_l_ ,Onn q ,0000 -, 0 0 07-Pq7 . Uo ,0_7_ . (.pTq -,0305 oOnn 7 -0001 -,0004
-. 7 _ .oo .1 7 q F .np_4 - . 0 23 5 .On 0 6 - .O00P - . o eo41.54 -bO . ? 7 01 . n _o5 - .olql .Onn_ - . 0 0 0 3 - .no n33,7P ,00 ,3ara ,_3o_ -,0140 ,000 2 -,000 3 -,0007_ . q _ .CO .4 7 _ 7 .n _ lP - .OO PO ,onno - , 0 004 -. o0 0 qP,l n ,00 ,_135 ,0713 ,0000 - ,Oq nl -,o00_ - ,OOC _
10, 4_ .Go .6 04 F . Oq n _ ,O lO l - ,On07 - ,oOl a -,OOP O12,7_ -._;_ ,710_ . l_p_ ,0_5o -.Oo n 3 -.ooao -,0 07_14. q _ - .0 2 .TP a _ . .l a _ .0_05 -.O o nP -. ( ,Oh 3 -,OILS17.20 . . 0 3 .t 7f . P .Pa= = .C70P - .00 3 _ -. ObTP -.01 2q1_,_ 7 ,oO ,q_ 7F .37? n ,on2 0 -,0n7 2 -,OOA] ,O01P
1.El , UC .}7_ ._na -,OIPP .0{105 -,0003 0_00
_t_ Eo
ALr FA _E TA e L CD CP C pw CYN CS F
1 .14 _.0_ ,IP_F . nl_l . 01 3 1 . Onl 3 .00 5 1 -, OOIP-_,h_ _, C2 -,lF7 l ,n7o = -,01 07 -,On S ,0 085 ,n 3flp-3,40 S .0 2 -.t .731 ,Opt6 ,O CIP -,0015 .007_ ,01_5-1,1e F ,e_ .o_rP ,OIQI ,OO P7 -.o ono ,006_ ,00_1
l.ll _.0 ) .17{:3 . o 1 _ 0 .0130 .0 o ]_ ,OObl - .OOln3 ,3q 5-e 7 ,7_47 ,n lO _ ,0193 ,oon4 ,o0_ -.noP7_._P ,OZ ,_F3 = .0773 ,0_74 ,ONTO ,eO_5 -.Ol_q7.7q _,0_ .3_72 .nan_ .0 3_ q .O NTO .OOe_ -._)_ 3 3
10,03 _,01 ,45G3 .nF;6 , 0477 , 0{1_3 ,006 9 -,03_P1_.31 4 ,Sq .E',gq ,to31 ,06_8 ,OlPP .00 71 -.n53a14.54 4._7 . 64 ; _ . 1 3 _ .o_1 ,011 7 .O0_P -,071716. PP a . b_ ,7_71 .lOlS . I 0 5 7 ,OoT T . nOl_ - 07 4_19, 14 F ,Ol ,paq q ,p_O .IPqq -()o3_ ,( .o 63 -.0761
1 . 1 7 c . n_ .1 7 1 r .OI _ P .nl 3 ? . _nI F .o o b| -. 00_ ;
8/12/2019 ersen nyilazott szrny orrsegszrnnyal val aerodinamikaihatsa
25/70
TABLEAll. - CONTINUED. 19
_U_ 30
_LPP_ pLIA _ L CP CP C_v CYP CS F
1.13 le. Or .1;53 .n? n; .0151 .OOP 3 .012 9 .O00E- 5 . _0 In . O_ -.1 4 P r . r_42 - . 0 13 _ -. 0o7 3 . O1 7q . 0_ I I-2.25 10 .1'6 -.053P .O?q_. -.0024 -.on4_ .0161 .038_-1.I_ j_.Oe .03F4 .npP3 .005 7 -.Oop7 .0141 .Ole3
1.19 IQ.OE .IE57 .n_ n4 .0150 .00 ?3 .0130 .OOn53 .4_ I 0 . 05 ._ 1 7_ .OP_I .0_4_ .once .O 1 2q -.0 1 7_
5.55 1_.04 .304P .r_4 .0354 - O IP_ .OI3A -.0 3537. P5 _ . 03 .3 9 4 0 . n4p_ .0 4 P2 . OI F O . 01_ 4 - . 055 4
I0.11 Io. OC .4P_7 .0701 .0_50 .O jpP .O1 7p -.OeS_IP.4 1 q .q_ .5P12 .1036 .OPI3 .0 714 o0165 -111 71 4.6_ _.g 7 ._ P_7 .147 6 .I01 0 .Opol .0160 -.13 2 P
16.q_ -q_ .7_1 3 .Pn3P .1251 .0145 . 0175 .142P1g . 25 In .n O . _7 . _76_ .1 544 . 00g 3 . 0155 -. 15g ]
1.1_ _ .u5 .12_ .0?ol .0154 .Oop5 .0130 -.0005
_LPP_ p ET_ C L rp _P c _. _yp C_ F
1.0_ .on .lb O_ ._17 1 .o146 .O nN_ -.OOO p -.OO C_-5. 7 0 -_0 -. I P 6_ .O4_P 0103 .Oon9 . 0 0 01 - .0004- 3.4 7 .o C -.0_7= .Opa6.00E5 .0010 .0000 -.00 0 S-1.23 .UO -.Obl l .0;lo ,010 6 .UOn g -.0001 -.0003
l.O5 .00 .0_0 .0 171 i0146 .O00R -.OOUP -. 0003
3.3_ .00 .iq_9 .nlPP o l b_ .bOO6 - .0001 -.O00P5.57 .00 .E7_O .opt4 e211 .OooP - .o00S .0oOP7.76 ._0 .? Cr .n4pO 0307 .000_ -.no0 1 -.GO00q.q3 .11 0 .4_ 10 .(,_ 044 1 -.Onol -.1_00_ -.0020
12.2 3 -.03 .514P .ri m3 ? .n54_ .O n p 4 -.0027 - .0 1 1114.44 -.04 .(,037 .1P07 .0716 . OOpq - .0057 -.OI7S16.74 -.o 4 .700P .1_ 77 .OP_P -.oopP -.007S -.o]7q1P .q_ -01 .7_44 .PLY4 .lOng -.0 070 -.0066 .0043
l.Oq .o0 .IOPF .01A7 .015 1 .Onoq -.0003 . 000_
_U_ 32
_LPF_ mi Te CL CP C P Cpu C_h C_F
l.O P . 0 0 . o q g 7 . n l _l .01 4 7 - 0008 -.0003 .0000-5,_q .00 - .IP74 .0_4S -.010_ .0010 .0000 .0000- 3 .44 . 0 0 - . 0q 7 4 .n? n_ . 0 0 2 1 .O_ ll -. O00 p - . 0 004-1.2_ .00 -.001_ .ep ]_ .010 3 .Oong -.O00p .00 00
1.07 .00 .0q74 .n iP 3 .GI_5 .000P -.ooo 3 oO OCn3.33 .00 .lqlO .npnl .01_ .Ono _ -.po03 .O00l5.57 .00 .2 7FP .O_7P .oP0 3 .OooO -.ooop 00017.75 .00 .255_ .04?4 .O$BP -.00o1 -.0003 -.no0_
10.01 -0o ._34= .oS_3 .03P4 .0001 -.0010 -.OOP P12.2_ -.02 .5_6 .OP?_ .0495 .00ig -.0035 -.nln_14.50 ..04 ._ ;_5 .11_ = .0613 .0027 -.0071 -.016416.77 ..04 . 723P .I_FI .0741 -.00;3 -.007_ -.016_19.04 .0 0 .P llq .P1 75 .0914 -.0057 -.oOb6 .0003
1.09 .00 .1010 .01Pl ._1 4_ .O00 P - .0004 -00 03
P L_ 33
_LPP _ pET_ CL CD C_ Cn _ Cy_ CFF
1.52 .00 .2_18 . 0_67 -.0_04 . 00q8 -.000 4 -.0004- S . 24 .00 -.015E .n410 -.0436 .oolo -.000_ -.0001-3.0 _ .00 .07 23 .0_34 -.03 1fi .Oon_ -.000_ .0001
-.78 .00 .164_ .03J3 -.0 _41 .Onn P -.0004 .00001.53 .00 .P60 E .0347 -.0207 .000 7 -.0005 -.no033.77 .00 . 34 7 1 . 04 P8 -, 0171 * 0 0 0 2 -. 0004 . 00 0 3
5.97 .00 .4__ .n_61 -.0 125 -Oonl -.0003 .O00l8.20 .00 .51EP . 07_3 -.00 63 -.Oon4 -.000 5 -.O00 p
10._3 .00 .5P57 .n_ .0065 -.oon2 -.o011 -.001_12.69 ..0_ .674_ .1_7_ .0 1 7_ .Onl _ -.003_ -010314.96 -.04 .77 1 3 .171n .0304 .Onl_ -.0075 -.O lE _17.20 --03 .P6 5P ._P 30 .04 70 - .One7 -.007_ -.013319 . 4 0 .Off ._ ] p .27_ .0675 -.On e4 -. oo4 P - 0020
1.5P . 00 .F6 3 _ .n q4_ -.070_ . Qon7 -.0005 -. nO01
8/12/2019 ersen nyilazott szrny orrsegszrnnyal val aerodinamikaihatsa
26/70
TABLEAll. - CONTINUED 20RU_ 3 4
ALPHA F&Ta CL CP C_ Co L, _y V C_ F
1,5 1 .Oo ,2_ IS . O_P _ -,D20 R .0007 -, OON_ -.O00B-5.2A .00 -,0 1 6 7 ,nAn? -. 0 43 N ,O 01l ,O00 I -, O0 0 P-3,00 .00 .0 71 6 ,O)P _ -.03 17 ,Oo n q -,O00I -.O00B
-. 7_ .D O .1 6 2 F . OPQ7 -. 0 2 _ 6 .O o nq -,D O0 ? - , 0OOF1 ,51 ,0 0 . 25_? . 037_ -. OPO_ , Oo n7 -. nO03 -. O00 B3 ,76 ,00 . 2 4 57 .o_O p -,0 177 . Oon _ -.0 0 0 5 ,0 0 0 1
5 .g_ ,uo . 4_ 2 F .OF ] 6 - . 0 1 19 -.Onn l -.000_ ,000_8 , 1B ,00 ,_Oql .0743 - , 0046 - . 00 03 -.O00a -, 0 00_
10,3q -, 01 . 57 @q .OQn n . 0090 .OnO3 -. COIl -. OOP6
12 , 65 -,0 3 .66 7 _ . I PP O , 0 2 13 ,0 0 19 -,o0 3 6 -, 011714.q0 _. b4 .75P _ .173= .03 g_ ,On l 7 -,00 52 -,Ol_q17 . 12 ., C4 . HE35 . 2 7 7 P .05 5q -,On_ b -, 0 0 73 - . 0 15 119 . 37 ,01 , q2P7 ._0 ,0 772 -, 007 _ -.0 0 5 7 .O 0 4 P
1 ,51 , 0 0 ._6 1 4 .037_ - .OZOg .C007 -.0003 - .0007
_UK 35
ALPHA mETA CL CP C X Cp u CYF CS F
1,0g F .0 3 .1 05_ .Ol ql .O I 2B , 00 03 .005g ,OOP_- 5 . 67 F .U4 -.17q7 . P 4 _4 -.OIl q -,0035 .0093 ,03_0-3,46 5.03 -.O PP1 .0315 - .000_ -.Onl_ .n0 83 .0 2_2- 1, 22 c,O 3 .0 0 5 _ .07 ? 6 .OOe P - , 001 3 .0o 7 3 , n121
l.OP =. U3 .104 3 .nlqO ,0129 .O on3 ,O05q ,O0_P3,3_ F.02 . lOlq .n_ ]7 .017_ ,0n36 .o055 -,n066_.5_ c. O_ .277 0 .e3 n2 .0 2 _4 ,O o_ ,0055 -.0 1A 47,75 _ .,02 .257_ ,n44_ ,03a3 ,Oohq ,O0_F -,017_
I_,2 F 5 .0_ , 51Pl .o_ q3 .06 3 0 ,0 0 _ 7 .00 51 -,n 3 e lI_._ _.00 .6 0 _ 4 .l P no , 0 7 6 F , Onq_ , 003_ -,0_5_1 6. 72 0.uO .6_ 7 0 ,Ia_7 .O q 4_ .00_5 ,005_ - , 0 01 61_,01 F,o4 ,eo_ .P3o1 ,11_5 ,OoA4 ,OOq7 -,0_37
1,0_ :,0 3 , 1 _ 5 1 ,nl_ ,0 131 ,0o04 ,o05g ,0023
\.
_l'k 36
_LPv e n tt_ CL r n C_ Coy CyF C_ F
],ll 10,_ ,113_ .nP_ .0 127 ,001 1 ,nl_O ,00 70- E-FI Im. Oc -.1 5 P C ,_=?n - . 0 1 6P -.00 77 .n 1 9: .06qn-2. 4 0 I O.(;P ,O_5 F ._c -.OOA g -.Cn4_ .OI Po .0 4 _1-I. 1 6 _0, 07 .O? FC .0 7 7 2 .O0 2 A -, Un pl .015Q ,02AP
1,11 lO,U_ ,1 1 _ ,_747 ,0126 ,OnlO ,o 13Q ,00713,37 In,06 ,I_G_ , pp71 ,O_lq , 0 0 5 q ,013? -,01055 ,_ ] 0,0 5 . _Q I _ . n_: ? .030q . 0110 , n1 3 1 - , o P TY7,63 _,u_ ,377p ,n_n a ,0420 ,O IJ_ ,n 13_ -,04 16
1 0.05 I n. Co , _5_ 7 . 07 _ , 0F93 ,0 1 _ 3 , 01 1 6 -,05qa12,30 in,0 3 .5_ .lnl ,07_ P ,01_6 ,01 37 -,0_ ?14,5 2 in , [.? .63E P .13P_ . Og_ F ,0 1 19 ,OIBl -,O_ P_16.81 _0.(2 4 .74 FE .lm74 .1070 ,O l&O .0 243 -, l lt q1_,1 3 Io.04 .p4F4 ._4_ ,12_3 ,noo_ .n 266 -,1 2_1
1.11 1r-c6 . 115a ,np4 7 .012_ ,001 1 .0141 ,006_
_L_ 3 7
_LP P_ mE T& L Co C_ Cu u CYP C cF
1.17 .u_ .1_7 .PI_; .0204 .00 11 - .o00_ -.ooo_-5.iF . co -.l_'l q .o_p_ -.co 22 ,un_)_ .o00 1 -,00o_- 2 ._: .O h -.0_ 2 C .n?_P .OOg4 .Ooi_ ,0000 -.0 0 0_-1 .1_ .uo .020a . n il6 ,0171 .o)[I ,COO n -,_Oq:
1.12 .o0 .1_30 .n]_ .n205 .Ohio -,tOO2 -,000_2, 4 _ .Uo ._12_ .fpn a ,0_ , o nlo -.0003 -,0o0?r F I , GO , _ q _t . q ] ] _ , 0 _ _ 7 _ ,00 0 7 - ,00C3 - , 0 00_7._2 .bF .57_; .0=_ .CEC4 .00 01 -.OOO= -.001 1
1C. I _ .U C ._&O ._7_ P .07 71 ,nnn5 -.001= -.Or)I P12._c ..01 .Fr l,;' _ .)p_ .lOO P .Un]_ -.0037 - .06_414.77 _.07 .71qC .IP_ .13_7 .On lv -.noep -.ol_n
19 .7o -.t' Z ],(_7_ ._ 74P .lqOq -.U D_ -,IOPS - ,_07 P
l . l _ . Vf, . i_ . r l C_ , . O_ O_ , t Oll -,O(*b? , O00_
8/12/2019 ersen nyilazott szrny orrsegszrnnyal val aerodinamikaihatsa
27/70
TABLEAll. - CONTINUED 21
P ( ' h 3 P
_LPH_ _ETA CL CP CN C_ CYP CS F
] . ] 4 .ON .12_F . N]6 7 . 0 _07 ._(l g -.NUO_ -. O0 0l
-E. h l .o C -.1 7q 7 .n_PP - . O0 33 . ON] O -.O 0 0 P .O00R- 2 . 4 2 - . _0 - . DFP_ . np_ = . 0089 .O0 P -.ODOP . O0 0 n-l. lg . 0 0 .01_7 .n]P3 .ole6 .O o l O - .OOO_ .oono
l.IA . oO .1 _4 1 . n I ?O . 0206 . Ono q -. 00 0 3 .fl O003 .40 - q (} .2 151 . o P t 4 .0 254 .Ooo q - .0 _ 03 -. oO o 2
_ . _ . UO . Tq_ .n 3 1 7 . 0 3 45 . Onn5 - . 0004 -.0 00_7._I . o 0 . 3P 1 7 .n4_ I .n4F7 . o nn2 - . 000: -.flOllI0,17 ,(JO ,_ 9 41 .0 7 7 7 .Ob96 . N()o_ -.oGI 4 -,O0 1 N
17.51 ..GI ._1o(; ,IPYO .oq40 .0013 -.()0 4 n -,006_14,_3 -. t)? ,74e7 .1Phi ,1227 ,Onl3 -,0067 -,0 11_17 . 7 _ -.('2 .Fc 3 T .? c _l . 1521 - .00 ? 0 -.OOPB -.01 4 51o._ 7 -.03 l .e 4 n_ . 3 _1 .IFO C -.nq 4 _ -.n06 3 -.Olll
1. 14 . o O . ] Pf 2 .I )IF P . OE0 7 . Oo n P -.000 3 .O CCN
ALPFA pE T_ Ct. CP CF' Cp . ._ CYP C_F
1.5_ .{JO . F Fl_ .n 3 aP -.OIZA .Onn7 -.nO0_ .non4-5,2a .oO -.0 1 23 .0_ -,0351 .(; On(_ -. o O0_ .0_0 3-2.q_ .00 .e_2_ .ePe_ -.n2Z q .00_7 -.0003 .OGO4
- . 7 3 . 0 0 .1P 3 3 ,oppP - . 0167 ,Oqn8 -.000 3 . 0 00 31.55 .00 . 27g_ . n3 a l - . 0127 .Onn7 -. O0 0 _ .nne_3 . _F . _0 .3 _ 7 . 0 4_ P - . 00_ 0 . 0 0 04 -. 0 0 0_ -.00016.04 .oO ._ 31 .0_ 03 .0034 . OonO - ,0003 -.0004_.2q .u_ .%cTt _ .07q_ .ollq .C _)O -,0005 -,000_
10 .63 .00 .e71_ .J P_ .0361 .OonP - .0017 - .O0 |l1 3. 00 . . U2 . 7 ' 3 7 3 . I n 0 3 .062 7 .Oqn_ -. nO4 P -. 00 _15.3_ ..u_ ._ IfF .;a_4 .e g:4 -,On o_ -.o07fl -,010717,_7 -,03 1,03_0 ,_P .1314 - ,Oq_O - .00_ -.011 _?0.0 . ,0 3 I . IR_ O .4 1 _? .16s6 -,00_0 -,O06P -, 0 11_
1.56 .UO . _F_F .OY_ - .0 1_ ? . Oo n7 -.000_ .0 0 03
rt.K 40
ALP P A FEI a _L r n C_ C_ , CYP CFF
1 .5_ .CO ._7Pl ._p C - . 0 1 _6 . 0 0 1 0 -.0003 -.noo?- 5 .21 . uo -.0 1 24 .n3 Fn -.0 34 B . oo o_ . 0 000 -. o oop-2 . q7 . on .Oe lf .npP4 - .02 2g .O()n q -.{) 001 - . 0 0 03
- .7_ . 0 0 .1_ 4 e .n_ Tq -. 01_8 .ol )] o -. oOOP . O0 0 p1.54 .O0 ._7_ 3 .0331 -,01_5 ,O nlO -,000_ -.OOOl3,80 .UO .3633 .04&_ -.0057 .0007 -, 0005 -,O0_l6.0_ .00 .445_ ._o l ,G055 ,O00P -.0003 -, O00P8 . 2@ .00 ._27_ . OVP_ .014_ .00o1 -,O00A -.0016
10._? .( } 0 ,_3_ .]2_ ,o411 ,Oon l -,nol_ -,001113 .00 .,0_ ,7e 7_ ,]p_7 .07 00 ,00_0 -,O04P - ,007_15,30 - .o3 ,qll_ ,p_3 .1G3 8 ,OO l5 - . no7 n -,013117,6q -,u3 1.0461 .341A ,1_07 -,ooPe - ._oe_ -,01_12 0. 1 7 -.Or 1.215 1 ,_77 . I 7 1R -.0o_5 -. OUSq -.00_
1 . 5 7 .1} 0 .2 E1 7 .0_30 -.U 121 .oo in -. no 03 -.o0oi
ALPPA mETA CL C_ CW Cp_ , CYF CS F
1,1_ 5 .oE ,1_70 ,0175 .OPO0 ,Oonq , 00_ ,nO on-5,6_ _ ,03 -,167q ,03_ -.00_ -,0040 ,OOe_ ,OEq7-3,_ 0 5,03 -,07e l ,OPq_ ,o06_ -,0037 ,0054 ,Ole?-1,1_ :,02 , 02_ .nln: ,0148 -, o017 ,no47 ,o oBP
1,1_ _.op ,1 2_0 ,Ol? _ ,o19_ ,_NN9 ,0041 ,OOOO3.3 _ _ . 0_ .213 _ .N P P _ .0 277 .t _ ( _ a _ . 00 4 2 -.0 0 775,61 _,0_ ._q6 C ,03_ ,0 41q , O07b , o04 n -,OlSa7. 8_ F-o0 ,3ql_ .n=pq .0 5 96 .OlIR7 .n0 5 4 -,03_7
10,10 _.q 7 .S _R7 ,07_ ,07 _5 ,n lO0 ,0 05_ -,056_12,50 4,q4 ,_ 121 ,l? _g ,lOqP ,0 134 ,005? -,07q614 ,_ 4,q4 744e , lpq7 ,1 41R , OIPP -,_OP q -,OgO617 ,_0 4.q4 ,e777 .;_70 .1730 ,Onn3 -,o0 5_ -,10_119.7_ 4 .96 l,oel P .3777 ,lqOl ,O{iqO - .005_ -.lI P3
1,13 : ,o_ .1_ 57 .O lTF .0_O l ,oniP .oo_n -.oCO5
8/12/2019 ersen nyilazott szrny orrsegszrnnyal val aerodinamikaihatsa
28/70
TABLEAll. - CONTINUED 22
_L_ 42
ALP P_ pt TA C[. CP CP Cp _A fyV CS F
1 .IF I0,0 5 . 1 3_0 ,0 ? 1 7 . O_6 P .O o I P , OI Gq - . 0005- 5 . 60 ] 0 , 07 -.1 4_7 .N _ p & - . 0 1 1 4 -. 00_3 ,n 1 4_ .0 57 0-3 . 35 10.06 -,0_5P . opqO . 0 0 T7 -.O n6_ .0130 . 036P
- l , I E 10 . 05 .040 F . n Pp2 . 0 1 2q -. oo3 n . 0 1 1 _ .01 7 11.1_ 10.05 . 1 3 2 P . 0?17 .0 _? . 0016 .o l lP -. OOO=
3.4_ 1 0.04 .P3_ .O_P6 .0415 .0o_ ,ol lP -.O _I P5,70 In ,03 ,3300 ,n_ 6 ,0603 .OIP_ ,011_ -, 04617 . 9 4 1 0 .00 .4 P7 1 .OtiS2 .07 9 3 .0154 . 0 11 7 -. 073_
lO,Z_ q ,96 ._277 , nqn O .1054 ,0177 .0091 -.1112IP . F_ q . 91 . _43 1 . I Pn O . 12 9 P . 0730 . 0 0 7 0 -. 15P71 4.9 0 O . q_ .7 #7_ ,l q l m .1 5_ 3 .01 75 . 0 0 17 -. 1 7C _17. 20 q . 9_ . 9 1 27 . _ 7 _4 .IP 6_ . 01 1 _ . 0 0 2 0 - . I 0 3 61 9.8 0 . 97 1 .0 _ 2 0 .3 7 70 . PI l O .0052 - . 0 01 5 - . 2114
1,17 10 ,05 ,13_l .0P 16 ,OZ70 .onl_ ,01 10 -,oon p
rb k _3
ALPP_ mEl_ CL C D Cv Cmu _ YP _F
1.04 . 00 . 0_ 61 . nP P 3 , 020_ , 000 7 . n O0 2 -. O00F-5 ,79 ,00 -,_183 .ncq q -,0126 ,O nn _ ,000 1 -,O00P-3,54 ,u O -.IPE_ .0433 ,0013 ,0010 ,o00n -,0007-1.2P .00 -.olq3 ,o3PF .0 12 1 . 00 0 7 ,0ooo -,_00_
1,03 ,o0 ,0F45 .OPP3 ,0208 ,000_ ,0002 -,00073.33 .o n .I_51 . n312 .02_ .OooP ,o00n -.00035,57 ,00 .PS lP .n 4nP ,0371 ,000 3 -.O00 P -,00037.7q ,00 .3711 ,0_ _ ,0473 ,OnnP -,o0o3 -.0007
1 0 . 06 -,01 .4 5F0 .07F_ ,0 635 ,On02 -,000_ -,OOE_]F,2P -,0 2 ,5361 .flq 6_ ,O80 A ,00_0 -,0030 -,00q 414 ,4_ .,04 ,6065 .1702 ,1 023 , OhiO - ,0053 - ,n 15316,83 _,Op .7440 ,IP7 _ .13B0 -,0014 -,0066 -,OOq 619, 2P .00 ,9030 ._7_5 ,1653 1,0 _77 - ,P O6p ,000 3
1,03 ,00 .OPFI .oPT q ,0211 ,Ono_ .0001 -,CO03
_Uk 6 4
ALPH_ pi T6 CL f_ CM _pM CY_ OFF
1,03 ,00 .Op4p .n? ?q ,0210 .Oo n_ -.0001 -.000 3-5,7q , 00 -,E17_ .n_n4 -,0135 ,0007 -,0001 ,0001-3,52 .00 -,IE?? .0430 ,0011 .Onnq -,ooop -,000 3-1,29 ,00 -,oE31 ,0330 .0 132 .Oo n_ -.0001 -,000 2
1.03 .00 .0_43 .OP P2 , 0_0 9 ,O( It)R -,000 1 -,00023,3_ .00 ,1_7P .n 30_ ,0270 ,OonP -, 000 1 -,000 35,60 .00 .p07_ .n3q 3 .o341 ,0000 . -,O00P -,o00 37,_3 ,00 ,3_P3 .0_40 .042P -,00o 3 -,nO0_ -.oOO R
lO.Op -, Ol ._70P ,n73_ .056P -.On o2 -.O01 P -.OOP P1_.3_ -,0_ . 55_? ,oo_4 ._719 ,Ont) 6 -,o03P -,00_11_.54 .,03 ,_3_ ,IPP1 .0915 ,Ono_ -,005_ -,014316,he .,0_ ,7_0 ,IP PP ,133_ -,OO l_ -,0070 -.00_ PlC,3I -,01 ,q15 5 ,?F _P ,159 2 -,0 05_ -,005_ -,o02n
1.04 .00 .OrP l .02PO ._213 .non 7 -.O00P -.OOOp
FUk 45
_LPP _ p ET_, CL CP _ Cq ,_ f. YN C=;F
1.4q . oo ,pf41 .o '3 v - ,0125 . Onn(- -,0002 -,0001=.2 _ .0 0 - . 0 3 _. .0_41 - . 0_ 50 .O nn6 - , O00p , 0001
-3,OF ,00 , 0_/'1 ,O4_P ,0305 ,0005 -,O00 P . ,00_1-.f_4 .oo . ] ,_ ,04 |3 . o_00 .ONo. _ -._o0_ ,oo01
. _.... 4 . o/. 37 01_4 ,00o. _ -,eo0_ -,OflOp3.7 F . OC .3F . _ 'q .00 32 00 6 5 ,0001 -10003 ,OOfl O
, 6,0. r - .00 .6r_7 .oFq4 0003 -,ONI )_ -,0003 ,0000F ._7 .00 ,r -4 jO . )P(_IF O 1P3 -,OI)O0 -.0005 -eGO07
10.57 -.01 .FS] I .1143 0 ZF, f-, -.000 _ -,o011 -. 0 0 2 7]p.TP .,u; _ .71Pq .141 c 040G .000 4 -,0033 -,oOg ]i 4.90 - 03 .794 P . 177n . e6 4_. - 1)onq - . e034 - . 0 ] P7l 7.24 . (;_ . _7_ . _&PF * ] 002 * (-IIt _q -- . r| 0 _ .'_ -- . D o_r;t:1 q*_v - ' b l 1.0t'90 .3FO4 1 4r '7 -,OOZ E -.no40 -,OPt*7
]..t.O .(in .p .r. 7F .0437 - ,G1_4 ,0005 -.0003 -,00C4
8/12/2019 ersen nyilazott szrny orrsegszrnnyal val aerodinamikaihatsa
29/70
TABLEAll. - CONTINUED 23
I:;UF 4_
ALPF_ pL Ta ('L C P C w CpM CYP CSF
1,4e ,oo , ;-4c )o ,n4 36 - ,ollq ,0007 ,OOn l -,o(}1_-5.2 _ ,0 -.O_' Oq .n_SF -,0450 .Oo oq .0000 -,oOOq-3 .OF ,00 ,OS4 F . q,44 . -,0316 ,OOnR ,0001 -.0010
-.P_ .o n .l=O q .n,nq -.o _on .oo07 ,0o01 -,O01l1.47 ,u o .P4 f 3 .04 37 - .01_1 .Onn7 .O OOl -.00173 ,77 ,00 ,34F7 ,05 :_7 -,00 40 .Oon 5 ,noon - ,00076.03 . 00 ._4 7_ .P? 03 .0020 ,onnl - ,eO 0_ -.GO0_8, , ;E . OO ,.=. 3 4_ , nat, =_ ,0155 , oono -, n o0 3 - , 0 01 3
]0 ,4 7 . ,O l , F If--_ , ll 4 P . 0 3 0 4 -,no n 3 - ,O00B -, 11 0 3f- .I P. 7 3 -.u3 . 7o o 0 .i .. 1q .C4 7q . Oon8 - . no3 ] -.ol i n14.q 2 -,04 .7777 .1741 , ('7 3P ,Oo n6 -,i}0o7 -,017017,3_ -.OF ,q _9_- .:_=: _ .4 .10 64 - .('033 -,O0_] -.007319 , 7 7 .O N 1 , 06 2 & . 7 4q;3 ,1 46 2 - ,o n t o5 -,o05 f . , 00 1 7
1 . 50 , no , _540 , n4 3 7 - ,0 1 17 ,()no7 , 0 0 0 1 -,00 1 P
_ t ; I x 4 7
ALP FA uE T_ ('t CP Cf_ CpP. , (-yp v CSF
1,0_. _, 0 . , 0 P75 . {} 31 f ,01_ 7 -, On P5 ,00_# , ,n l Jl- 5 ,7p =, o_ - , ? I 4 F , n_ . 3 _ - , 0 14(, - , one 7 , n 074 , 04 3 3-3 , =- F . = , 05 -, 11P 3 ,l4q -' _ - , 00 07 - , on so ,006 5 ,0 3 2 3- l, ? -. ' .- =, 0_ -, e l bC . n S F .; . 01 0 3 - ,On 3 6 ,n0 5 4 , o_ Z. 1
l,O.r :. t;r: .OF re . Oai 7 .t}lq4 -,0024 .0043 ,01333 ,3 4 =* 0-= , I I _- ; : . n3 4n , n_ 7 .'i -,Onf1 3 ,o0 3 5 , 004 05.61 _ o{ : f. ._P? 7 , n ,.,. , 0 3 0 ? , On lo , on3n -,00 177 .F_ O _ .t' F .3 ( .PI . I) _- _ . 0520 .O, s F .O 02P - . 0 C6 _
1 0,04 c.. O& . 4_ 1 4 . 0707 . n(07 ,(,077 ,n Ol 0 -,0 1_31?, 34 _* O--= ,_FI O , In_q .Oq{l ,O t I Ql ,noo n -.037414.59 ,.';in ._r_r ] 14r'_ . I P06 .Onq4 .nO l_ -.0_501 6 . O_ 4 .5 4 . 70= . 1q 07 . 14 37 ,0n73 . OOZ'4 - . Oq l 71g. 33 4, 9 7 .q14 1 -;_7 _'_" ,1710 [_;11]q , O04 7 -,0q 63
1,04 r ''O= . OP7.) .031_' . 01 r ;_ -, O nP,4 ,0043 ,O12P
rUN _
ALFP _ ofT# L C_ C P Cn _ CYN CF F
1 .05 ] o . lq .o q o_ . h 3 7 n ,0207 -,One5 ,O]Oq oO_F_-5 , 7 3 I n , ll -, 1q9_ . n_ q 7 -. o1_ 4 - , 0 1 4? , Olb q . 0_6_
-3 , 4@ ]n- lo -.1014 .oF| q - . 0 0 46 -,01_4 ,0145 ,OF*I-1._3 .n,lo -.eOb_ .n4 1_ ,00_ - ,Oon_ .ol_6 ,045a
1,0 5 Io ,l O , 0_94 , n_n , 0_07 -,0n_6 , 0 11 0 , O_q?3 .33 In ,lo . 1_7 .o4n4 ,0333 -,Ooin ,olOp ,fllSn5,5 a l O*ll . P TP _ , 04 q 4 .0_ 7 ,0 () i_ ,O O9 _ -,0 0] _7.P4 l _,lo ._77F ,0 674 .07_4 ,00_ ,00_ 7 -,O_S q
I0 ,I _ I, , 0 7 , 4FC F .nn31 ,0960 ,0 11 0 ,n0 9 7 - ,05 6712 , 4 0 i 0 , 04 , F OI7 . IP ql , I_ E7 ,nlSp ,oog 3 - , _q C_14,76 1 _,Ol , 71 OP .171 0 , 1 5 27 ,0115 , no 77 -, ] _ I _1 7, 1 4 q , _ 7 . P =O_ .?_?_ .1 7 3 4 .O l i n .0 07 3 - ,I FF 4
1,o+ l e ,l O .OGI_ . n 3 7P .OEOQ - .0065 .nlOn oO _n_
RUk 4 9
ALPP _ _t1_ CL q_ Ct ' CO,_ CYP CSF
1. 17 . 0 0 .13 01 . olvo .ooOu . 0005 - . ooop - . 000 7- 5 ,5 9 ,00 - , 1 4 9 1 . n HTF - ,0 _6 7 ,O on_ - , n o n4 - ,oo0_-3 ,34 ,00 -,n540 ,o p41 -,o1 35 ,Oon_ -,no04 - ,OOe P-1,10 - 00 ,04 03 ,_17 P - . oo_o .oo, ) 6 - . no u 3 - . non_
1 ,17 ,uo , 1 _ 9 4 ,n l _ a , 00 80 , oqn5 -, OOU? -,0 0 0_3 .3_ ,00 ,PI P_ ,qP o3 ,n]5_ ,coo p -.oOop -,000_5,@1 . bO ._qlP .027q ,OPE 3 .1)0 00 ",000_ --,OO n_7 , Rp ,00 ,2 75 P , o_ n l , O_ P4 -,O oq 3 -,nO0_ -,O0 1F
10,05 ., 01 ,4 fS E ,n_ o= ,0351 -,POol -,oola -,n0 3 112.3 n -.01 ,_n l .on_q .04P7 -.O qll -,003_ -,00_
14,53 .,0_ ,63_F ,IP_O .n_2q -,on1 3 - , o05 3 -,010016.80 --01 ,73 _0 , 1_o_ .07_.q -.0n7 3 -,0067 -, O05p1q,17 -,Ol ,_4 73 ._470 .OqPI -,0n7 3 -,nOe l -,0030
I,I_ ,00 ,130P ,01_7 ,OOP 3 , On n4 -,O00 p -,0004
8/12/2019 ersen nyilazott szrny orrsegszrnnyal val aerodinamikaihatsa
30/70
24TABLEAll. - CONTINUED
_U_ _0
ALPP_ p El_ CL cn C P CpH CY W C_F
1.17 .uO .130P .n169 .0081 .00o5 -.O00_ -.0007
-5._P .00 - .14_ .0373 - .0267 .Oqn 6 -.rO04 -.oooP-3.3? .00 -,0534 .0?_0 -. 0133 .On09 -.0004 -.0000-I.11 .00 .04 (_S .n 177 -.002 1 .On06 -.000 3 -.no07
|.18 .00 . 129P ool6q .0079 .Oo nS -oOOO p -.oo u73,41 . OO ,P IE4 .qP 04 .01S 6 .Onn3 - ,000 ? -.nO075.6P .00 .291 q .O_7q . 0221 . 0001 -. nO0 3 -.00117.U1 .00 .374P .0400 .02_6 -.Onp4 -.0005 -.0014
lO.OR -.01 .463_ .n6n 7 .035 0 -.Oonl -.0015 -.0031IP.30 _.02 ._3_4 .OP _m .0487 -. 000 7 -.n 03_ -.006714 .55 -.02 .f 315 .129_ .06E7 -.0016 -.005 6 -.n0 9616.82 -.Ul .735_ .1An q .07 _6 -.0075 -.007_ -.n 04619.13 .00 .P403 .?4_ .o97 e -.0n77 -. 0084 -.001_
1.17 .00 .131_ .nl_n .OOP3 .no05 -.o00P -.0004
nUk _1
ALPHA pLT A CL Cn CH C UP CYP C SF
1.17 .00 .1314 .O]Tfi .0083 .OOn 4 -.0004 -.0004-5.5 e .00 -.1 489 .03 AO -.0266 .On 08 -.0005 -. O00 R-3.33 . o0 -,053_ .n?4_ -.0134 .Oon 9 -.ooo A -.OO lO-1,10 , 00 ,0 39q ,0]o4 -,o0]q ,0007 -,0 004 -,0006
1.14 .00 .12e7 .olnl .0080 .0005 -. 0004 -.000_3,39 ,o 0 ,212E ,o?1 _ ,015 9 ,oon2 -, oou4 -.ooo _5.61 .O0 ._q17 .o Pq l .0_26 .O000 -.OO0 5 -.OO ln7,no ,00 ,37 60 .N41_ ,02q3 -,0 004 -,000_ -,OOlq
IO.O P ..01 .4670 .06P2 .0338 -.0002 -.0015 -.O03 P12. 32 -.02 ._4_ .n_TP .04 47 -.Oon _ -.0033 -.O 07m14.4q -,02 , 615_ ,l? Oq .06_4 -,O op5 -,0 05] -, 010616.69 ., 0_ ,6_6_ ,I_P ,090_ -,OoA6 -,007 _ -,00731_,q8 , 00 ,TPP_ ,P _3P ,11 0P -.0 067 -,0085 -,0 01_
l.lP . ,o O .]31_ ,nl7? . 00_ 3 .000 4 -.000 3 -.O0 0S\.
PUk _2
ALPM_ pET a CL CO C N CR_ CYP C SF
1.18 .00 .132P .0171 .0002 .Oon 4 -.O00& -.no04-_.59 .00 -.14qe .n 3_l -.0267 .0007 -.0005 -.ooc_-3.3_ .O0 -.OS_O .O p4_ -.0137 .uonq -. 000_ -.000_-1.13 . O0 .0 400 .Ol_ -.0023 .00 _7 -.O00_ -.0004
1.16 .00 .1301 .0170 .O07q .000_ -.000_ -.00033.40 .VO .pl4] .0;1 _ .0157 .On0 3 -.0003 -.000 35.b 4 .00 ._9_4 .q pq_ .O_2P .(_onO -.nO0 5 -.00077.R_ .00 .3_1 .043 & .0_ -.OooP -.11007 -.COl&
10.06 -.Of ._0 .06?7 .034h -.Onn b -.t_O l_ -.002_IP.32 -.o2 ._4q F .o_q .0448 -.Onn5 -. o03n -. on7414,4P -, 02 ,61 5_ ,I?&6 , 065_ -,00_3 -,005 0 -,OOP 616.73 -.UI .703_ ,170P .OP _I -.00_4 -.0078 -.00_
_l,h _ 3
ALPP _ pLT _ CL _P C_ CgM CyV C_F
1.2 5 .00 .13 02 .0176 .O07R .0 003 -.000 _ -.00C6-E.7S .00 - .]65 _ .o_nl -.02q 7 .ono3 -. 000_ .0000-3._0 .00 -.003_ .OP_ -.014_ .Oon 5 -.000_ -.o003-1.1o .o0 .033q .hin t -.o o2_ .ooo5 -.hO OT -.oOo_
1.24 .00 .]_67 .017P .0074 .00113 -.0007 -,00063.56 .O0 .214P .07]_ .OlStl . CooO -.0007 -.0003S.P3 .00 .Pgq_ .o3nn .0231 -.00_4 -.O0o? -.000_R.II .00 .3_ 6P . 043 = .02_6 -.Oon 7 -.0007 -.0011
10 .44 -. 01 ._837 .e6_ .0361 -.0006 -,001 5 -.00 3312.74 -.04 ,_65F .no42 .o_o2 -.oooS -.oo31 -.nlO014.9S - . b_ ._34_ .13_ ? .0756 - .On e7 -.0084 -.016 3
17 ,3e .,Op . 7_ .lq _ .oqo3 -,Oo3P -oOlOW -,n? 07
8/12/2019 ersen nyilazott szrny orrsegszrnnyal val aerodinamikaihatsa
31/70
25
TABLEAll. - CONCLUDED
ALPh J pETP C L ?P CV C_Pv C YP C_F
1,3F ,00 , ?05_ .n?_P -,0068 ,0001 -,0005 -,0004-5,35 ,00 -,05P2 .0742 -,0435 ,0007 -,0006 -,000 _-3,0c ,UO .0 35P .OP4q -,0 598 ,Oon 6 -,000 6 -,000 _
-,Be .00 ,I _IF .OP30 -,0176 .00 07 -,0006 -,00031,3_ ,00 , 204_ ,073 0 -,0070 , OOo E -.0004 -,nO053._1 ,00 ,2854 ,n_oo ,00] -,O nn2 -,000 _ -.ONO_5,81 ,00 ,3647 ,04n0 ,OOeO -,0004 -,000_ -,00068,0? ,00 ,451 0 .n _ ,0135 -, 0005 -,0007 -, 001_
10,2P .,01 ,_397 , OP02 ,ol q_ -,Oon_ -,0013 -,n0 2512,_1 -,02 , _171 ,lOP7 ,0320 -, S no _ -,0034 -,007716. _? .07 .F604 .1 _0 .05P q -.00_6 -.00 70 -.O0? Q16._P .0_ ,7663 ,10 41 .0766 -o0_51 -,0084 -oOOgq
ALpP_ =LTD (L ?m CV CoN CYw CFF
1,_5 ,00 ._740 .0 _46 -,OZOg ,Ooo O -.00 06 -.000 7_,1_ ,00 0732 .037_ -,OSbO OOn_ -,nO0 _ -,00 0_
-2.HP .bO .] IUP .0_11 -,0440 ,O ff05 -,PO0 _ -,000]-.71 ,00 . lC ;e .e_ n = -,03 EU ,Onn3 -.n 004 -,na_ClI _ .Vfl _723 .0_4 -.0209 _ qi 1_ -._004 oO00n-, .
3.77 .o0 .3523 .n 4_O -.01 35 ion l -.n 004 -.00 036 0 | ,(I0 .433_ ,n=_P - .006 # Onn3 -,nOO_ - .0006_._p .00 . T?4| . OTCE -.O0 2R 00 06 -.O00R -.O0] O
10. 66 ..01 . e c r_ .1o15 ,00 5_ -,8no 6 -,oo 14 -,oo3 _1_._7 ..0 _ ,6771 .13P0 .021 0 -.0o16 -.003R -o007414 ,_ -,U3 ,74_0 ,174F .0_45 -,Onlh -,0067 -.011317.07 ..0 2 ,8 _qP .pP_3 .063_ -,0_4 0 -,O0_q -,0O_n
ALPP _ pET _ CL CP C_' CpF , CYP C SF
1.36 .00 .2007 .n _l_ -.0030 .00 03 -.0004.0000
-5,41 ,0 0 -._P? p .n _ -. 11 6 9 .(,f)nR -.no 0_ i0000
-3.1_ .00 .OlO_ ,0737 -,015 1 .PO O4 -.000 3 000_-.93 ,00 ,1 056 .OJ q7 -,O0 6P ,0002 . -.0004 000 ;1.33 . o0 . 1 9 94 .opjn -.00 30 .O on? -.o004 00o?3.5_ .o0 ._7P _ .0_73 . O02P . 000 0 -.O00S 00015.7_ ,00 ,3576 ,O_P O ,O OP7 -,0 003 -.000_ - 0002_ . 0 1 . o0 . 4 4 4 P . _ 43 oOl_U -.0oo_ -. 0 00 4 0 0 05
lO ,3F .,01 ,53+P . OTVP .0_37 ,0002 -,0015 -,00_41 2 . 5 3 .,0_ . 6 31C .llnl , 0356 ,0000 -,003 q -,0 06_1_ .77 ., 0_ .72 _0 .1_? _ ,0531 - o0007 -,o06 n -, OOq ?17.06 .. 03 ._OE .7nvl .07_1 -.0n31 -.n07 _ -.0111
P Ub 7
ALPF_ _ETD CL _D CV Cp u CYP CFF
.7 5 .00 . 0014 .0 1 F 6 . 01_ . 0010 .00 00 - .n OOn-6,53 ,00 - ,=O lq .P417 -,8103 .Oon3 ,0000 -,0002-4.30 .00 -.I0 7 ? .0273 .0 031 oO00 h .0000 - .0004-2.04 .o0 -.010 5 .01ol .o llq .0o0 8 .000 1 -.O00F
,25 . 00 ,0_13 .01_ F ,0167 .On ll .CO On -,0010$,_ ,bO .]P OI .OJ _Z ,O) _g ,O00g - .0001 -o00114.70 .0 0 . _ 57 _ .n ? _3 .0E 4 9 .On o_ . 0000 -. 0 0 1_
6,93 ,o0 .3303 .03_ 7 ,0331 o0OO 7 .no00 -,00199,21 .,01 , 433P ,n 570 ,0419 o001 7 -,0007 -,0 037
11 .4_ . ,0_ ,F43P . onpP ,05_4 ,Onto -,001 -,OOPP13,74 - . I' 3 . _4 FP .1P qJ ,060o .On p o -,005_ - ,OIPo1610 .,03 ,7_0 ,IR7? ,078_ oOOnP -0090 oO l3q
8/12/2019 ersen nyilazott szrny orrsegszrnnyal val aerodinamikaihatsa
32/70
26
REFERENCES
1. Robins, A. Warner; Morris, Odell A.; and Harris, Roy V., Jr.: Recent
Research Results in the Aerodynamics of Supersonic Vehicles. J. Aircr.,
vol. 3, no. 6, Nov.-Dec. 1966, pp. 573-577.
2. Robins, A. Warner; Lamb, Milton; and Miller, David S.: Aerodynamic
Characteristics at Mach Numbers of 1.5, 1.8, and 2.0 of a Blended Wing-Body
Configuration With and Without Integral Canards. NASATP-1427, 1979.
3. Coe, Paul L., Jr.; and Weston, Robert P.: Effects of Wing Leading-Edge
Deflection on Low-Speed Aerodynamic Characteristics of a Low-Aspect-Ratio
Highly Swept Arrow-Wing Configuration. NASATP-1434, 1979.
4. Coe, Paul L., Jr.; Huffman, Jarrett K.; and Fenbert, James W.: Leading-Edge
Deflection Optimization for a Highly Swept Arrow-Wing Configuration. NASA
TP-1777, 1980.
5. Coe, Paul L. Jr.; Kjelgaard, Scott 0.; and Gentry, Garl L., Jr.: Low-Speed
Aerodynamic Characteristics of a Highly Swept, Untwisted, Uncambered Arrow
Wing. NASATP 2176, 1983.
6. Gillis, Clarence L.; Polhamus, Edward C.; and Gray, Joseph L., Jr.: Charts
for Determining Jet-Boundary Corrections for Complete Models in 7- by
lO-Foot Closed Rectangular Wind Tunnels. NACAWRL-123, 1945. (Formerly
NACAARR L5G31.)
7. Pope, Alan; and Harper, John J.: Low-Speed Wind Tunnel Testing. John Wiley
& Sons, Inc., c.1966.
8. Carlson, Harry W.; and Walkley, Kenneth B.: An Aerodynamic AnalysisComputer Program and Design Notes for Low-Speed Wing-Flap Systems. NASA
CR-3675, 1983.
8/12/2019 ersen nyilazott szrny orrsegszrnnyal val aerodinamikaihatsa
33/70
27
TABLE I. - GEOMETRICCHARACTERISTICSF MODEL
Wing:
Aspect ratio ........................................................ 1.838
Reference area, m2 (ft 2) ................................ 0.863 (9.293)
Gross area, m2 (ft 2) .................................... 0.949 (10.210)
Span, m (ft) ................................................ .260 (4.133)
Root chord, m (ft) .......................................... .674 (5.492)
Tip chord,m (ft) ........................................... .161 (0.529)
Referencemean aerodynamicchord, m, (ft) ...................0.895 (2.937)
Leading-edgesweep, deg:
At body station 0.530 m (1.738 ft) ...............................3.02
At body station 2.027 m (6.651 ft) ...............................0.0
Verticalfin (each):
Span, m (ft) ................................................ .107 (0.350)
Root chord, in (ft) .......................................... 0.326 (1.069)
Tip chord,m (ft) ........................... ...............0.048 (0.158)
Leading-edgesweep, deg ............................................ 3.4
Taper ratio ......................................................... .148
8/12/2019 ersen nyilazott szrny orrsegszrnnyal val aerodinamikaihatsa
34/70
C
L CDWind
Cy
Windc_>
X
Figure 1.- Systemof Axes,
8/12/2019 ersen nyilazott szrny orrsegszrnnyal val aerodinamikaihatsa
35/70
I b j
L_o.53o2-7o_o-"---_ "',,I (I,38) I.220 _ i_ : O.895-_,
(4.002) -' _371 ' "',,_ I. 7 5 6 f_ '(5.60) I_ \-_ 41.46,
= 2.02 7 _ _n o_,,,,, . _( 6 . 6 51) -1 '
2.487 __(8.1 6 1)
( L_I
a = 0 Referenceine_
Figure 2.- Three View Sketch Of Model. Dimensions Are Given In MetersAnd Parenthetically In Feet.
8/12/2019 ersen nyilazott szrny orrsegszrnnyal val aerodinamikaihatsa
36/70
2.375 _ i2.326 (7.793)
_. 2 .054 (7.632)I
2.027 (6.738) 53.69 (6.651) O.3132.108 (I. 028
(6.91 7) _[
AO.530(1.738) 73.02 Hinge-line
m m
L_ 0.680_ (2.230) 2.204 _ 0.242I - (7.230) -- (0.795)0.061 O .179
SectionA-A SectionB-B (0 .200) (0 .589)
_40 deflection normalto hinge-line
Figure 3. - Details Of Leading- and Trailing-Edge Flap Systems.Dimensions In Meters (ft) Unless Otherwise Noted.
8/12/2019 ersen nyilazott szrny orrsegszrnnyal val aerodinamikaihatsa
37/70
b
Slat I
Configuration I1I ii _" Shimhickness_
-- -I
Slatelement '6Le _" 6Le* cm inches
(_ 35 20 .254 .100
(_) 35 35 .254 .100
(_) 35 35 .254 .100
35 35 . 27 .050(_ 30 30 .076 .030
@ 30 30 .076 .030 __ /(_) -
normaltowing, ding-edge (_J /_
6Lemeasuredo increases latg p _- -'--__ ._._.
_Sh im ins erted ea
_racket locations
SectionA-A typical
_:=_51at brackets allstreamwise
(b) Leading-Edge Slat
Figure 3. - Continued
8/12/2019 ersen nyilazott szrny orrsegszrnnyal val aerodinamikaihatsa
38/70
2.375=_. 2.054 17.632) I I B
:_ 2.027 (6.738) _ -___ /,,,_;"- _ 56.651) 3.69 o
A " A /
.65 . .(1.7 38) [-_
2.2 04 _ 17.230)SectionA-A SectionB-B
_deflection instreamwisedirection
(c) Variable Chord Leadin g Edge
Figure 3,- Concluded
'
8/12/2019 ersen nyilazott szrny orrsegszrnnyal val aerodinamikaihatsa
39/70
___] P itot-s ta ticrobe
-- ,-- ,_ IttI-" ,_ 111---] 2.13
'_ (7 O)| I O.1.52 / /I/
O.300 _ I. 086 (0.500) //,_l
(0.984) "__. 563) /J i (3. 46 )
,' , / l i ' ii
Turnta bleI
O.69 7__(2.292 )
Figure 4. Model mountin g arrangement in Texas A & M University 7-X lO-footLow-Speed Wind Tunnel. Dimensions are in meters and parenthetically in feet.
8/12/2019 ersen nyilazott szrny orrsegszrnnyal val aerodinamikaihatsa
40/70
8/12/2019 ersen nyilazott szrny orrsegszrnnyal val aerodinamikaihatsa
41/70
12 1.0
.o_ _ 0 0 ._ .c,_ _ . s_ [] 30 s "'------- o ,o _.- ._
-.o_ 0 40 .2
-.08 0 "
1.0 12.0
_ i _o_2 L LID J _ 2.o1
F _\ .-'28 -q 0 u_ 8 1 2 16 20 0 .Oq .08 .12 .'16 .20 .2_ .28 01. .2 .3 . ,5 ,6 .7
c_leg CD CL
(a)Vertical fins on, 6f - 0
Figure 6.- Effect Of Simple Leading Edge Deflection.
8/12/2019 ersen nyilazott szrny orrsegszrnnyal val aerodinamikaihatsa
42/70
8/12/2019 ersen nyilazott szrny orrsegszrnnyal val aerodinamikaihatsa
43/70
12 .0
04 .6 r
Cm S
o . _ _ - P [] 30 .4 ,_
- . o__ _ ,s ; _ 0 40 .2- .08 0
1 . 0 , 12 .0
Z ,o . _ f 6.0 _ ; _
0 _ - ,.,_ 2.0
-.2_ _ Ll O 8 1 2 16 20 0 .04 . 08 . 1 2 . 1 6 .20 .24 . 28 C .2 .3 . 4 . S .6 . 7
_,_g CD e L
(C) Vertical fin s on , 6f - 20
Figure 6. - Continued
8/12/2019 ersen nyilazott szrny orrsegszrnnyal val aerodinamikaihatsa
44/70
12 _j 1.0
.o6 _ / _. 6IF, deg ._
.o_ _ _,_ ..o/ [] 30 _0 _ .4
40-.Oq _ .2
-.OB O
/ oi.o .. _. 12.0
8 _"S - io.o
Lfb2 _ _ _ q.O_ _ 2.0
-'28 -_ 0 4 8 12 16 20 0 .0_ ,08 .12 .16 .20 .2_ .28 01 .2 .3 ._ .5 .6 .7
a ,deg CD CL
(d)Vert icalfins off , 6f - 20
Figure 6. - Concluded c
8/12/2019 ersen nyilazott szrny orrsegszrnnyal val aerodinamikaihatsa
45/70
39
Figure 7. - Tuft Photographs of the Configuration With SimplyDeflected Leading Edge (_LE = 30u)"
8/12/2019 ersen nyilazott szrny orrsegszrnnyal val aerodinamikaihatsa
46/70
8/12/2019 ersen nyilazott szrny orrsegszrnnyal val aerodinamikaihatsa
47/70
12 _ Z 0 1.0 j.08 ] _ Leading-edge //_ _-. ._._ 0 Undeflected . .
[] Slat, i(see fig . 3b) s
-.o_ _ Slat , 1 (seefig. 3b)
-.08 0 n
I.0 12.0
' ,ooy 8 . o \N
_ _ 2.0-'2-8 -q 0 u , 8 12 16 20 0 .0 .08 .12 .16 .20 .2 u , ,L:>8 0.1 .2 ,3 .u, ,5 .6 .?
a ;ieg CD CL
(b} Verticalfins off, 6f - 0.
Figure 8. - Continued
8/12/2019 ersen nyilazott szrny orrsegszrnnyal val aerodinamikaihatsa
48/70
12 ( / 1.0_I Leading-edge .8o_I / _ Undeflected .6 / _ %
am :_ .:r [] Slat , l(see fig. 3b)..o...o3:_ , ._I
-.0ul o ._ .2_cr
-.08 0
12.0
"_ " S ' /_'_--,. /_ / _ -- 6.0 /
0 "' 2.0
-'28 -U. 0 _ 8 [2 16 20 0 .04 .OB . t2 .J.6 .20 .2u , .e8 0 /. .2 .3 ._ .5 .6 .7
_leg C D CL
(c) Verticalfins off, 6f - 20.
Figure8.- Concluded
8/12/2019 ersen nyilazott szrny orrsegszrnnyal val aerodinamikaihatsa
49/70
43
Figure 9, - Tuft Photographs of the Configuration With Leading Edge Slats.
8/12/2019 ersen nyilazott szrny orrsegszrnnyal val aerodinamikaihatsa
50/70
12 Io0
f_' Intersegment oints .8 -,'"-_ _o8 / _
/0 Sealed i
0_ ,6,_ _. x, -_x''_- /] Unsealed so ,_ .. /oI
-.0_ .2 _,8
- . 08 0
1 . 0 12 . 0
' j ( "%LiD ,
2 m Lt.OI
./, -Oo'2-8 -4 0 8 12 16 20 0 .0_ .0 8 ,12 .16 .20 ,2u_ ,28 ,1 .2 .3 ._ ,5 ,6 .7_g CD eL
(a)Slat I , verticalfins on.
Figure 10. - Effect Of Sealing Intersegment Joints Of Leading Edge Slat Configurations. _f =0
j
8/12/2019 ersen nyilazott szrny orrsegszrnnyal val aerodinamikaihatsa
51/70
12 i .0
.o8 _ Intersegmentoints .8 _ :_="'_ _-
.o. _ 0 Sealed
o _.._ [] Unsealed s ._-. o_ . 2 o
-.08 0
1 . 0 12 . 0
8 _ _ -_ ] o - _
_ __ 11_ _o . oe f _0 ,,i 8.0
.,. / l =.o .,.,o _ ,. 2.0
o/-'2-8 -_ o _ 8 12 Is 20 o .o_ .o8 .12 .is .2o .2_ ._8 1 .2 .s ._ .s . e
a_leg CD CL
(b) SlatI, ver tica linso ff
Figure 10.- Continued
8/12/2019 ersen nyilazott szrny orrsegszrnnyal val aerodinamikaihatsa
52/70
. 2 1.0
OB .B
.o_ __. 0 Sealed
cm _ _,_ .6o _ ..-_ [] Unsealed s .4oi-.0_ '- ,2 0
1.0 12.0
8 n _ , I0.0 :_
.s _ =f. 8 .0_14 -- s .o -x
f .._,,f _.oo/-'2_ 8 _u , 0 LI 8 12 1 6 20 0 .Oq .OB .12 ..16 .20 . 2q .28 01 .2 .3 .q .S .6 .7
a,deg CD CL
(c) SlatI I, verticalfins on.
Figure 10.- Continued
g I
8/12/2019 ersen nyilazott szrny orrsegszrnnyal val aerodinamikaihatsa
53/70
.12 I i .D I oO
.oB Intersegmentoints .B / _, ,.o4 j_* Sealed .6
[] Unsealed s _='_-0 4 0-,04 .2
- .08 0
1.0 , I 12.0
/ -e ,_ _ f _ _ 1o .o "_ -" \.6 =i- ,_...- o.oC1
o._s _ _.oJ-.2, -4 0 8 12 16 20 .04 .08 .12 .16 .2D .24 ,28 O. 1 .2 . 3 .4 .5 .6 .7
_e_ CD CL
(d) Slat i , verticalfins off.
Figure I0.- Concluded
8/12/2019 ersen nyilazott szrny orrsegszrnnyal val aerodinamikaihatsa
54/70
12 1o0
.o8 Slat configuration .8 , ._.
._ / Nominalsetting / "_
o o ._- [] Largegap(seefig. 3b) s ._ J.o_ of _ Largegapwithoutboard-.oe wingpanelgapsealed .2_
I .0 lS.O
.o ,'," 8.o / _x_/ / -,,,.
, j /. oo/D \o :r 2.0
/ oi.2__ -4 o _ 8 12 is 20 o .m .o8 .12 .Is .so .2_ ._ . .2 .3 ._ .s .s .
_g CD CL
(a)Verticalfins on .
Figure11. - EffectOf Slat Gap. Slat I.
8/12/2019 ersen nyilazott szrny orrsegszrnnyal val aerodinamikaihatsa
55/70
12 I.O
Slatconfiguration :t'_'_""_
oo "/ "--,_ _ _ "_ 'f o Nominalsetting] Largegap(see fig. 3b) s
0 .... _ Jt_r
o , _ Largegapwith outboard @.0_ .2wing panelgapsealed
-.08 O
0 12.0
8 _f" - 8.0CL / f o.o '_
2 4.0
o = f 51 2.0oi
-'28 -_ 0 tl 8 12 16 20 0 ,0_ .08 .12 .16 .20 ,2_ ,28 01 , 2 .3 ._ .5 .6 .7
_,deg CD CL
(b) Verticalfins off.
Figure 11. - Concluded
8/12/2019 ersen nyilazott szrny orrsegszrnnyal val aerodinamikaihatsa
56/70
12 .0
_> 5LE,deg g,,.0_ ._ 0 0 ._ _. __--__
o _- 0 40 _ -.Oq .2 []
-.08 0
1.0 _ 12.0
.a -./" Io.o _
CL. 1 _ 6.0 _ "
o %R-'2B I_- _0 q 8 12 16 20 0 .b_I01_ .08 .12 . 16 .20 .2tt .28 01 .2 .3 . q .5 .6 .7
=,deg e D G L
(a)Vert icalfins on, 8f - 0.
Figure12. - EffectOf VariableChord Leading-EdgeDeflectionOn LongitudinalAerodynamicCharacteristicso
8/12/2019 ersen nyilazott szrny orrsegszrnnyal val aerodinamikaihatsa
57/70
I B
12 1.0
.o, , _ o 0 \[] 20 s -':__
- . OLi .2
-.08 0
P
' i
- 28 -_t 0 U , 8 12 16 20 0 .OLI .D8 .12 .16 .20 .2_ .28 .2 .3 .ti .5 .B ._
a , de g CD CL
(b)Vertical finsoff, 6f - 0. o l--.1
Figure 12. - Continued.
8/12/2019 ersen nyilazott szrny orrsegszrnnyal val aerodinamikaihatsa
58/70
. :_ I.O
.o8 ._/o 6LE,deg .6 .._. --_.o, _ 0 0 .6 _ f_-'-'_-_-----cm _ [] 200 ,4 /
40 ._-.0
0
-,08
1 . 0 1 2 .0
I0.0
.s .40 8.o
6.0 "/ "
o-'2-8 -4 0 u , 8 12 1 6 20 0 .OU_ .08 . t2 .1 6 .20 . 2u , . 28 0. .2 .3 . . 5 . 6 . ?
_,des' CD' CL
(c) Verticalfins on, 8f 20.
Figure 12. - Continued
8/12/2019 ersen nyilazott szrny orrsegszrnnyal val aerodinamikaihatsa
59/70
8/12/2019 ersen nyilazott szrny orrsegszrnnyal val aerodinamikaihatsa
60/70
54
=8
(a) aLE = 20.
Figure 13, Tuft Photographs of the Configuration With Variable Chord Leading Edge.
8/12/2019 ersen nyilazott szrny orrsegszrnnyal val aerodinamikaihatsa
61/70
55
a =0
(b) aLE = 40.
Figure 13, - Concluded.
8/12/2019 ersen nyilazott szrny orrsegszrnnyal val aerodinamikaihatsa
62/70
8/12/2019 ersen nyilazott szrny orrsegszrnnyal val aerodinamikaihatsa
63/70
.o, ._ 0 Undeflected _..6 "
[] Simpledeflection, 81F - 30 sO Slat I (seefig . 3b) _>-.Oq .2
A Variablechord,5IF- 2 0-.08 0
1.0
2 L /D "_q.O(
-'2-8 -u. 0 4 B 12 1B 2O 0 .04 ,OB .12 .IS .2 0 .L_ .L>B Ol .2 .3 . q .5 .B , 7
(x , d eg CD CL
(b)Ve rtic alfins o ff, 8f - 0
Figure 14. - C ontinued
8/12/2019 ersen nyilazott szrny orrsegszrnnyal val aerodinamikaihatsa
64/70
}2 1 .0
o Undeflected.o_ _ _ .s
c,_ ._G _ [] Simpledeflection,6LE=30 s /_
-.o_ _:___""
8/12/2019 ersen nyilazott szrny orrsegszrnnyal val aerodinamikaihatsa
65/70
12 1.0
.o_ _ 6 deg ._ _p___04 _ .6 o
o _ _, _ [] 10 ..'_
8/12/2019 ersen nyilazott szrny orrsegszrnnyal val aerodinamikaihatsa
66/70
.12 1.0
.o_ 0 .6 /
o > .v" [] 10
_ _ 20- .OB 0 O
1.0 12.0
10. (
2 _ _.(
o /o _ ,_ _'h 20
-'_-B - 0 u= 8 1 2 16 20 0 .O U= .OB .1 2 .t6 .20 . 2u = .2B O.1 .2 .3 ._ . 5 .6 .7
_x , d eg CD at .
(b) Sla tI.
Figure 15. - Concluded o
8/12/2019 ersen nyilazott szrny orrsegszrnnyal val aerodinamikaihatsa
67/70
Leading-edgeUndeflected
Simpledeflection ,6LE-"30Slat
Variable chord,6LE- 20
001-
I I I I I I I I I
0 .2 .4 .6 .8 0 4 8 12 I(5
CL o, deg o
Figure16. - InfluenceOf Leading-EdgeConfigurationOn EffectiveDihedral.
8/12/2019 ersen nyilazott szrny orrsegszrnnyal val aerodinamikaihatsa
68/70
1. Report No. 2. Government Acces s ionNo . 3. ReciPient 's Ca ta log No.NASACR-172531
4. Title and Subtitle 5 . Re port Date
EFFECTSOF LEADING-EDGEDEVICESONTHE LOW-SPEED FP hP ,,_Pv lqg,_AERODYNAMICHARACTERISTICSF A HIGHLY-SWEPT 6. Pe-_o rming _ rgan_ at ionCx)deARROW-WING
7. Author( s ) 8. Perfo ;m' _n'gO;gan _za; ionReport No.
Samuel J. Scott, Oran W. Nicks and P. K. Imbrie10. Wo rk Unit No.
9, PerformingO rganization Name and Address
TEKWORLDompanyDrawer 9005, Briarfield Station 11 .Con trac tr Gran tNo .Hampton, VA 23670 P.O. L-69215B
13 . Typ e of Repo rt and P e riod Covered12. Spo nsoring Agency Name and Addr e s s
Contractor ReportNational Aeronautics and Space Administration 14 . Spo nsoringA ge ncy CodeWashington, DC 20546 505-43-43-01
15. Suppl ementa ry N ote s
Langley Technical Monitors: Samuel M. Dollyhigh and Domenic J. Maglieri
16. Abst ra ct
An inve stigati on was conduc ted in the Tex as A&M Unive rsity 7-by 10-foo t Low-Sp eed Wind Tunne l to prov ide a d irec t com paris on o f the e ffec t o f seve ral le ad ing-ed ge dev ice s on the ae rod ynamic perfo rma nce o f a high ly-swept wing con figura tion.The tests were conducted over an angle-of-attack range of -6 to 16, for a Machnumber o_ 0.21 and a Reynolds number (based on the mean aerodynamic chord) of4.1 x 10U.
Analysis of the data indicates that for the configuration with undeflectedleading edges, vortex separation first occurs on the outboard wing panel forangles of attack of approximately 2, and wing apex vorticies become apparent for
> 4 . However, the occurence of the leading_edge vortex flow may be postponedwit-h leading-edge devices. Of the devices considered, the most promising were asimple leading-edge deflection of 30, and a leading-edge slat system. Thetrailing-edge flap effectiveness was found to be essentially the same for theconfiguration employing either of these more promising leading-edge devices.
Analysis of the lateral-directional data showed that for all of the conceptsconsidered, deflecting leading edge downward in an attempt to postpone leading-edge vortex flows, has the favorable effect of reducing the effective dihedral.
'_7. Key Words ( Su gg es ted by Author(s)) 18 . Distribution Statement
Leading-Edge Devices UNCLASSIFIED- UNLIMITEDSupersonic TransportsLow Speed Aerodynamics STARCATEGORY2 - AERODYNAMICS
19 . Se cu rity Cla=if. (of this report) 20. _=curity Cl as $if.(of this page) 21 . No. of Pages 22 . Dice
UNCLASSFI ED UNCLASSFI ED 66 A04
N-30s Fo rsa lebytheNat ionalechnicaln for mationer vice ,pr ingfield.irg inia2 161
8/12/2019 ersen nyilazott szrny orrsegszrnnyal val aerodinamikaihatsa
69/70
8/12/2019 ersen nyilazott szrny orrsegszrnnyal val aerodinamikaihatsa
70/70
Recommended