Mensa XE Mensa XE (Extra Efficiency) (Extra Efficiency) High Efficiency Family High Efficiency Family Airplane Airplane Michael Duffy Due: December 11 th , 2007 Georgia Tech – AE 6343 Aircraft Design I, Project 2 Presented to: Prof. Dimitri N. Mavris Honor 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."
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Mensa XE (Extra Efficiency) High Efficiency Family Airplane Michael Duffy Due: December 11 th, 2007 Georgia Tech – AE 6343 Aircraft Design I, Project 2.
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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."
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
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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 –
− 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)
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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.
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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)
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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)
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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)
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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
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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
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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
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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