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Mensa XE Mensa XE (Extra Efficiency)(Extra Efficiency)
High Efficiency Family AirplaneHigh Efficiency Family Airplane
Michael Duffy
Due: December 11th, 2007
Georgia Tech – AE 6343 Aircraft Design I, Project 2
Presented to: Prof. Dimitri N. MavrisHonor Code Statement: “I the above signed certify that I have abided by the honor code of the Georgia Institute of Technology and followed the collaboration guidelines as specified in the project description for this assignment."
2
IntroductionIntroduction
3
Introduction - RequirementsIntroduction - Requirements
Mensa XE is a High Efficiency Family Airplane A four seat, low-cost, high efficiency family aircraft. 20 year entry into service.
Design Mission: Payload: 2+2 Pax + baggage (400 + 240 + 160 lbs = 800 lbs total) Block Fuel Burn: > 30 miles per gallon Range: 700 miles (608.3 nm) Loiter: 45 minutes, end of mission
Performance Requirements: Cruise Speed: > 200 mph (174 knots) TOFL: 3000 ft, over 50 ft obstacle V_stall < 61 kts Stall V_TO >= 1.1 V_stall Takeoff V_CL >= 1.2 V_stall Climb V_A >= 1.3 V_stall Approach V_TD >= 1.15 V_stall Touchdown Climb: 300 fpm @SLS
Miscellaneous Requirements: Glass cockpit flight instruments VOR/ILS/GPS navigation w/on-board map Limited auto-pilot features (altitude and heading hold) Emergency parachute system, and air-bag system (Cirrus SR20/22 safety features)
Source (1)
4
Introduction – Mensa XEIntroduction – Mensa XE
Range = 700 miles
Cruise = 200 mph
Fuel Consumption = 39.7 mpg
Engine = 250 HP
V_stall = 51 knots
Take off distance = 2,227 ft
Landing distance = 2,817 ft
17
Conceptual Sizing and Synthesis Conceptual Sizing and Synthesis –– 33--ViewView
Graphical Model (3-view) FINAL DESIGN
38’
24’
6.5’ – 6 bladed
Wing Area = 138 ft.sq.
FINAL FLOPS SIZING AND PERFORMANCE RESULTS
OPERATING WEIGHT EMPTY 1506.7 LB
PAYLOAD 800.0 LB
MAXIMUM FUEL 136.6 LB
GROSS WEIGHT 2443.4 LB
REFERENCE WING AREA 138.00 SQ FT
WING LOADING 17.71 LB/SQ FT
THRUST PER ENGINE 419.8 LB
ENGINE SCALE FACTOR 1.0000
THRUST-WEIGHT RATIO 0.1718
Geometry:Span = 38 ft.Wing Area = 138 sq.ft.AR = 10.4Taper Ratio = 0.446Sweep = 7.0°Dihedral = 20°Thickness to chord of wing (weighted ave.) = 0.12
5
Conceptual Sizing and SynthesisConceptual Sizing and Synthesis
6
Conceptual Sizing and Synthesis - SummaryConceptual Sizing and Synthesis - Summary
Using project 1 sizing and synthesis Fixed Wing Conceptual Design Tool: Mission analysis (summary, table)
Constraint analysis (plot)
Final design point and estimated TOGW
Briefly Summarize sizing exercise and document key assumptions
Design point (from conceptual design tool):
− T/W = 0.14
− W/S = 17.0
− W_0 = 2,348 lbs
− W_E = 1,408 lbs
− W_C+P = 2,209 lbs
− Wing Area = 138 sq.ft.
− Required Thrust = 328.7 lbs.
7
Conceptual Sizing and Synthesis – Conceptual Sizing and Synthesis – 3-View3-View
Graphical Model (3-view)
38’
24’
8’ – 4 bladed
Wing Area = 138 ft.sq.
8
Conceptual Sizing and Synthesis – Mission AnalysisConceptual Sizing and Synthesis – Mission Analysis
Mission Analysis 800 lbs of payload
Take-Off Gross Weight = 2,348 lbs
Weight Empty = 1,408 lbs
* Note Source
Step 1 Payload Calculations, WPL
400 lbs240 lbs160 lbs
Total WPL 800 lbs
Step 2 Weight Take Off Guess Based on Historical Data, WTO_GUESS
W_E W_TO V_cruise Range(lbs) (lbs) (kts) (nm)
2,050 3,000 150 777 2,225 3,400 185 1,170
Average: 3,200 168 974 WTO_GUESS 2,348 lbs
Step 3 Mission Fuel Weight Fractions, WF
Profile Weight Fractions:W1/WTO 0.995
W2/W1 0.998
W3/W2 0.992
W4/W3 0.961
W5/W4 0.994
Total Fuel Fraction WL/WTO 0.941
Total Weight of Fuel Required WF 139 lbs
Gallons of Fuel 23.2 galMiles per Gallon 30.18 mpg
Step 4 Initial Operation Weight Empty, WOE
WOE 1,408 lbs
Step 5 Initial Weight Empty, WE
WTFO - lbs
WE 1,408 lbs
Step 6 Allowable Weight Empty From Historical Data, WE_HIST
A Regression Const. (Single Engine Prop) -0.144B Regression Const. (Single Engine Prop) 1.1162
Weight Empty from Historical Data WE_HIST 1,408 lbs
Step 7 Adjust Take Off Weight Guess Until WE = WE_HIST
First IterationWE 1,408 lbs
WE_HIST 1,408 lbs
Error (0) lbs
Loiter for 45 min. @ 5,000ft
Warm-up Taxi
Max Performance Take-Off @ SL
Max Power Climb to Opt. Alt.
Cruise out 700 nm @ Optimum Speed/Alt
Aircraft Type
2 Pilots
CIRRUS SR20CIRRUS SR22
2 PassangersBaggage
WOE = WTO_GUESS - WF - WPL
WE = WOE - WTFO - WCREW
9
Conceptual Sizing and Synthesis – Mission SummaryConceptual Sizing and Synthesis – Mission Summary
Mission Summary 700 miles range (608.3 nautical miles)
139 lbs of Fuel (23.2 gal)
30 mpg (Design requirement)
* Note Source
Seg. Description Altitude Temp. Density Velocity Range q CL CD L/D Wn-1/Wn Fuel Burn Fuel Weight Beta
(ft) (°F) slug/ft^3 knots nm psf (lbs) (lbs) (lbs)0 0 59.0 2.377E-03 0.0 - 0 0.0000 0.0097 0.00 1.000 - - 2,348 1.0001 Warm-up Taxi 0 59.0 2.377E-03 0.0 - 0 0.0000 0.0097 0.00 0.995 12 12 2,336 0.9952 Max Perforamnce Take-Off @ SL 0 59.0 2.377E-03 67.1 - 15 1.2000 0.1341 8.95 0.998 16 5 2,331 0.9933 Max Power Climb to Opt. Alt. 10,000 23.4 1.755E-03 73.2 14 18 0.9371 0.0611 15.34 0.992 35 19 2,313 0.9854 Cruise out 700 miles @ Optimum Speed/Alt 10,000 23.4 1.755E-03 178.0 608 79 0.2114 0.0113 18.78 0.961 125 90 2,222 0.9475 Loiter for 20 min. @ 5,000ft 5,000 41.2 2.048E-03 110.0 608 35 0.4559 0.0171 26.66 0.994 139 14 2,208 0.941
Mission Summary
10
0.0
0.1
0.2
0.3
0.4
0.5
0.6
0.7
0.8
0 10 20 30 40 50 60 70 80
Conceptual Sizing and Synthesis – Constraint AnalysisConceptual Sizing and Synthesis – Constraint Analysis
Design SpaceDesign Space
Design PointDesign Point
T/W = 0.14T/W = 0.14W/S = 17.0W/S = 17.0
Thr
ust
Load
ing,
T/W
Wing Loading, W/S
Take off 3,000 ft
, 50 ft
obstacle, V_stall <
61 kts
Lan
din
g d
ista
nce
3,0
00 f
t, V
_TD
>=
1.15
V_s
tall
Climb 300 fpm, V_CL >= 1.2V_stall
V_stall < 61 kts
Service Ceiling 15,000 ft
Cruise Speed > 200 mph
11
Preliminary Sizing and Synthesis - Preliminary Sizing and Synthesis - InputInput
12
Preliminary Sizing and Synthesis - Preliminary Sizing and Synthesis - InputInput
Construct Working FLOPS File
Convey information and assumptions form conceptual phase have carried over to FLOPS: started preliminary sizing with output from conceptual design phase: T/W 0.14 and W/S 17.0
What information (assumed or inferred) from the vehicle concept description Sizing Mission –
− Payload: 2+2 Pax + baggage (400 + 240 + 160 lbs = 800 lbs total)
− Block Fuel Burn: > 30 miles per gallon
− Range: 700 miles (608.3 nm)
− Loiter: 45 minutes, end of mission
Design Constraints –− Cruise Speed: > 200 mph (174 knots)
− TOFL: 3000 ft, over 50 ft obstacle
− V_stall < 61 kts Stall
− V_TO >= 1.1 V_stall Takeoff
− V_CL >= 1.2 V_stall Climb
− V_A >= 1.3 V_stall Approach
− V_TD >= 1.15 V_stall Touchdown
− Climb: 300 fpm @SLS
Source (2)
13
Preliminary Sizing and Synthesis - Preliminary Sizing and Synthesis - InputInput
Design Point − Started preliminary sizing with T/W = 0.14, W/S = 17.0
− Attempt to match the 329 lbs of thrust requirement
− 30 mpg
− Max Cruise Altitude =12,000 ft.
− 3,000 ft. runway
Geometry parameters (from output of conceptual design) − Wing:
• Span = 38 ft.
• Wing Area = 138 sq.ft.
• AR = 10.4
• Taper Ratio = 0.446
• Sweep = 7.0°
• Dihedral = 20°
• Thickness to chord of wing (weighted ave.) = 0.12
− Fuselage
• Length = 24 ft.
• Width = 3.44 ft.
• Depth = 4.59 ft.
− Vertical = 25.0 sq.ft.
− Horizontal = 23.7 sq.ft.
Source (2)
14
Preliminary Sizing and Synthesis - Preliminary Sizing and Synthesis - InputInput
Propulsion and power plant parameters:
− TELEDYNE CONTINENTAL MOTORS - IO-360-ES (X – Modified for 2,027 tech.)
− 250 HP (Modified for 2,027 tech.)
− Min SFC 0.35 (modified for 2,027 tech.)
− Six cylinders horizontally opposed
− Four strokes, Fuel injected, Spark ignition, Direct drive
− Air-cooled
− Wet sump engine, Incorporating a top induction system, bottom exhaust.
− Height 22.43 in.
− Width 31.46 in.
− Length 34.03 in.
Source (4)
15
Preliminary Sizing and Synthesis - Preliminary Sizing and Synthesis - InputInput
Aircraft type – Single engine, tail sitter, low wing
Aircraft class – Family four passenger
Percent of Materials used – Airframe 85% composites
Technology year - 2027
Intermediary and Final Calculations To obtain the required efficiency the RPM was varied to achieve 30 mpg
To obtain the required rate of climb the engine power was increased from 210 hp to 250 hp
To obtain the required take off distance wing CL max was increased to CL = 2.0
16
Preliminary Sizing and Synthesis - Preliminary Sizing and Synthesis - OutputOutput
17
Conceptual Sizing and Synthesis – Conceptual Sizing and Synthesis – 3-View3-View
Graphical Model (3-view) FINAL DESIGN
38’
24’
6.5’ – 6 bladed
Wing Area = 138 ft.sq.
18
High Efficiency Wing DesignHigh Efficiency Wing Design
High Aspect RatioHigh Aspect Ratio Advanced Feather TipAdvanced Feather Tip
Combination of advance Combination of advance tips and high aspect ratio tips and high aspect ratio balance Aerodynamics balance Aerodynamics with Manufacturabilitywith Manufacturability
19
Preliminary Sizing and Synthesis - Preliminary Sizing and Synthesis - WeightWeight
Weight Breakdown Table + user defined percentage of usage of composites and non-traditional
materials
Glass cockpit flight instruments VOR/ILS/GPS navigation w/on-board map Limited auto-pilot features (altitude and heading hold)
Emergency parachute system, and air-bag system (Cirrus SR20/22 safety features)
Source (3)
20
Preliminary Sizing and Synthesis - Preliminary Sizing and Synthesis - WeightWeight
Weight Breakdown
Emergency parachute system, and air-bag system (Cirrus SR20/22 safety features)
MASS AND BALANCE SUMMARY PERCENT WREF POUNDSWING 12.19 298
HORIZONTAL TAIL 0.00 0VERTICAL TAIL 0.00 0
FUSELAGE 20.09 491LANDING GEAR 3.69 90
NACELLE (AIR INDUCTION) 0.00 0STRUCTURE TOTAL 35.96 879
ENGINES 13.39 327THRUST REVERSERS 0.00 0
MISCELLANEOUS SYSTEMS 0.00 0FUEL SYSTEM-TANKS AND PLUMBING 0.82 20
PROPULSION TOTAL 14.22 347SURFACE CONTROLS 2.81 69
AUXILIARY POWER 0.00 0INSTRUMENTS 0.74 18
HYDRAULICS 0.33 8ELECTRICAL 0.41 10
AVIONICS (Includes: Glass Cockpit, VOR/ILS, Limited Auto Pilot 3.91 96
Emergency parachute system, and air-bag system (Cirrus SR20/22 safety features) 2.86 70
AIR CONDITIONING 0.00 0ANTI-ICING 0.00 0
SYSTEMS AND EQUIPMENT TOTAL 11.07 271
WEIGHT EMPTY 61.25 1,497
CREW AND BAGGAGE-FLIGHT, 0 0.00 0-CABIN, 0 0.00 0
UNUSABLE FUEL 0.25 6ENGINE OIL 0.17 4
PASSENGER SERVICE 0.00 0CARGO CONTAINERS 0.00 0
OPERATING WEIGHT 61.67 1,507
PASSENGERS, 4 32.74 800PASSENGER BAGGAGE 0.00 0
CARGO 0.00 0
ZERO FUEL WEIGHT 94.41 2,307
MISSION FUEL 5.59 137
RAMP (GROSS) WEIGHT 100.00 2,443
Structure 85% Composites:-Wing-Tail-Fuselage
Final WE = 1,497Final WE = 1,497Final TOGW = 2,443Final TOGW = 2,443
Source (3, 4)
21
Preliminary Sizing and Synthesis - Preliminary Sizing and Synthesis - PropulsionPropulsion
Propulsion and Powerplant Description of powerplant
− 250 HP
− Six cylinders horizontally opposed
− Low RPM (1,600 RPM)
− High Efficiency (0.35 SFC)
Number of Engines = 1
Placement – Front Mounted
Source (4)
22
Preliminary Sizing and Synthesis - Preliminary Sizing and Synthesis - PropulsionPropulsion
Propulsion and Powerplant Thrust vs. Altitude curves for varying Mach number
-
2,000
4,000
6,000
8,000
10,000
12,000
200 250 300 350 400 450
Thrust (lbs)
Altitude (ft)
Standard Day
0.28 0.24 0.20 0.16 0.12 0.08 0.04 0.00
Mach #:
23
Preliminary Sizing and Synthesis - Preliminary Sizing and Synthesis - PropulsionPropulsion
Propulsion and Powerplant Fuel consumption curves
-
2,000
4,000
6,000
8,000
10,000
12,000
0 0.05 0.1 0.15 0.2 0.25 0.3 0.35 0.4
SFC (lbsm/lbs hour )
Altitude (ft)
0.00 0.04 0.08 0.12 0.16 0.20 0.24 0.28
Mach #:
Standard Day
24
Preliminary Sizing and Synthesis - Preliminary Sizing and Synthesis - AerodynamicsAerodynamics
Aerodynamics Basic aerodynamic description of aircraft
• Span = 28 ft.
• Wing Area = 138 sq.ft.
• AR = 10.4
• Taper Ratio = 0.446
• Sweep = 7.0°
• Dihedral = 20°
• Thickness to chord of wing (weighted ave.) = 0.12
25
Preliminary Sizing and Synthesis - Preliminary Sizing and Synthesis - AerodynamicsAerodynamics
Aerodynamics Drag polar for varying Mach number (graph)
0
0.01
0.02
0.03
0.04
0.05
0.06
0.07
0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1 1.1
CD
CL
Mach = 0.2Mach = 0.3Mach = 0.4Mach = 0.5
26
Preliminary Sizing and Synthesis - Preliminary Sizing and Synthesis - MissionMission
Mission Performance: Mission profile (schematic)
* * * M I S S I O N S U M M A R Y * * *
INITIALSEGMENT WEIGHT(LB) SEGMT TOTAL SEGMT TOTAL SEGMT TOTAL START END START END
TAXI OUT 2,443.0 1.0 1.0 5.0 5.0TAKE OFF 2,442.0 0.0 1.0 1.2 6.2 0.1 0.0
CLIMB 2,442.0 8.0 10.0 11.8 18.0 21.4 21.4 0.1 0.3 0.0 10,000.0CRUISE 2,434.0 92.0 101.0 192.8 210.7 553.8 575.1 0.3 0.3 10,000.0 10,000.0
DESCENT 2,342.0 2.0 103.0 22.6 233.4 33.2 608.3 0.3 0.1 10,000.0 0.0APPROACH 2,340.0 2.0 105.0 4.0 237.4
RESERVES 2,338.0 32.0 137.0TAXI IN 1.0 3.0 240.4
ZERO FUEL 2,307.0
DESIGN RANGE 608.3 FLIGHT TIME 227.2
BLOCK TIME = 4.01 HOURS BLOCK FUEL = 105.6 POUNDS
ATA TRAFFIC ALLOWANCE = 46.8 NAUTICAL MILES AIR MANEUVER = 17.2 AIRPORT TRAFFIC ALLOWANCE = 17.4 AIRWAY DISTANCE FACTOR = 12.2
ATA RANGE = 608.3 NAUTICAL MILES
ALTITUDE (FT)FUEL (LB) TIME (MIN) DISTANCE (N MI) MACH NUMBER
17.6 Gallons
700 miles (608.3 nm)39.7 mpg39.7 mpg
TO @ SL, Standard
10,000 ft Altitude Cruise @ 200mph 45 min Loiter
Land @ SL, Standard
700 Miles
27
Preliminary Sizing and Synthesis - Preliminary Sizing and Synthesis - MissionMission
Mission Performance: Instantaneous cruise data:
WEIGHT ALTITUDE MACH NO. THRUST FUEL FLOW EX POW CLIFT LIFT L/D ENERGY VELOCITY TIME DIST FUEL T/TMAX SFC CDRAG(lbs) (ft) (lbs) (lb/hr) HP (lbs) (kts) (min) (nm) (lb)
2434 10000 0.27 198 29 372.4 0.23743 2434 12.314 11315 172.35 17.97 21.4 10 0.79193 0.14466 0.019282394 10000 0.27 198 29 379.1 0.23355 2394 12.117 11315 172.35 101.39 261 49 0.79165 0.14469 0.019272388 10000 0.27 198 29 380.1 0.23296 2388 12.087 11315 172.35 113.99 297.2 55 0.79162 0.1447 0.019272382 10000 0.27 198 29 381.1 0.23238 2382 12.058 11315 172.35 126.58 333.4 61 0.79159 0.1447 0.019272376 10000 0.27 198 29 382.1 0.23179 2376 12.028 11315 172.35 139.17 369.5 67 0.79156 0.1447 0.019272370 10000 0.27 198 29 383.2 0.23121 2370 11.998 11315 172.35 151.77 405.7 73 0.79153 0.14471 0.019272364 10000 0.27 198 29 384.2 0.23062 2364 11.968 11315 172.35 164.36 441.9 79 0.7915 0.14471 0.019272358 10000 0.27 198 29 385.2 0.23004 2358 11.938 11315 172.35 176.96 478.1 85 0.79147 0.14471 0.019272352 10000 0.27 198 29 386.2 0.22945 2352 11.908 11315 172.35 189.55 514.2 91 0.79145 0.14472 0.019272346 10000 0.27 198 29 387.3 0.22887 2346 11.878 11315 172.35 202.15 550.4 97 0.79143 0.14472 0.019272342 10000 0.27 198 29 388 0.22847 2342 11.857 11315 172.35 210.74 575.1 101 0.79141 0.14472 0.01927
28
Preliminary Sizing and Synthesis – Preliminary Sizing and Synthesis – Constraint AnalysisConstraint Analysis
Constraint Analysis: After completing the FLOPS
preliminary design analysis, the required thrust went from 329 lbs to 419 lbs
Keeping the wing area the same the wing loading went up to W/S = 17 to 17.74 psf
Conceptual Design Point
Preliminary Design Point
T/W = 0.14
TOGW = 2,348 lbs
WE = 1,408 lbs
Thrust = 329 lbs
T/W = 0.178
TOGW = 2,443 lbs
WE = 1,507 lbs
Thrust = 419
W/S = 17
S = 138 sq.ft.
W/S = 17.71
S = 138 sq.ft.
29
Preliminary Sizing and Synthesis – Preliminary Sizing and Synthesis – Constraint AnalysisConstraint Analysis
Landing Requirements: Take off, DFAROFF = 2,227 ft < 3,000 ft
Landing, DFARLDG = 2,817 ft < 3,000 ft.
Stall Requirements: STALL SPEED (VS) = 51.14 kts < 61 kts
1.05 VS 53.69 kts
1.20 VS 61.36 kts
Miles per Gallon = 39.7 > 30.0
Cost/AC = $58 Million > $150,000 Maybe I made a mistake?
ExceededExceededExceededExceeded
ExceededExceeded
ExceededExceeded
Not MetNot Met
30
ConclusionsConclusions
31
ConclusionsConclusions
Using the FLOPS program an aircraft with the range of 700 miles @ 200 mph was designed: The table below summarizes the key parameters for the Mensa XE
Further detail into engine design would be the next step, specifically: Efficiency
Fuel type
Engine size
FINAL FLOPS SIZING AND PERFORMANCE RESULTS
OPERATING WEIGHT EMPTY 1506.7 LB
PAYLOAD 800.0 LB
MAXIMUM FUEL 136.6 LB
GROSS WEIGHT 2443.4 LB
REFERENCE WING AREA 138.00 SQ FT
WING LOADING 17.71 LB/SQ FT
THRUST PER ENGINE 419.8 LB
ENGINE SCALE FACTOR 1.0000
THRUST-WEIGHT RATIO 0.1718
32
References:References:
(1) AE 6343 Aircraft Design Project #2, -2007, “Sizing and Synthesis with a Legacy Tool for Distance Learning Students”, Hernando Jimenez
(2) Flight Optimization System, Release 6.12, User's Guide, Revised 14, October 2004, L.A. (Arnie) McCullers
(3) http://www.cirrusdesign.com/sr20/features.aspx
(4) http://www.tcmlink.com/EngSpecSheetDocs/IO360G.pdf