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Mensa XE (Extra Efficiency) High Efficiency Family Airplane

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

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Mensa XE (Extra Efficiency) High Efficiency Family Airplane

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  1. Mensa XE (Extra Efficiency)High Efficiency Family Airplane Michael Duffy Due: December 11th, 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."

  2. Introduction

  3. Introduction - 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 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 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 = 10.4 • Taper Ratio = 0.446 • Sweep = 7.0° • Dihedral = 20° • Thickness to chord of wing (weighted ave.) = 0.12

  5. Conceptual Sizing and Synthesis

  6. Conceptual 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 – 3-View • Graphical Model (3-view) 38’ Wing Area = 138 ft.sq. 24’ 8’ – 4 bladed

  8. Conceptual 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

  9. Conceptual 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

  10. Conceptual Sizing and Synthesis – Constraint Analysis Design Space Landing distance 3,000 ft, V_TD >=1.15 V_stall Thrust Loading, T/W Design Point Take off 3,000 ft, 50 ft obstacle, V_stall < 61 kts T/W = 0.14 W/S = 17.0 Climb 300 fpm, V_CL >= 1.2V_stall V_stall < 61 kts Service Ceiling 15,000 ft Cruise Speed > 200 mph Wing Loading, W/S

  11. Preliminary Sizing and Synthesis - Input

  12. Preliminary Sizing and Synthesis - Input • 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 - Input • 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 - Input • 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 - Input • 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 - Output

  17. Conceptual Sizing and Synthesis – 3-View • Graphical Model (3-view) FINAL DESIGN 38’ Wing Area = 138 ft.sq. 24’ 6.5’ – 6 bladed

  18. High Efficiency Wing Design High Aspect Ratio Advanced Feather Tip Combination of advance tips and high aspect ratio balance Aerodynamics with Manufacturability

  19. Preliminary Sizing and Synthesis - Weight • Weight Breakdown • Table + user defined percentage of usage of composites and non-traditional materials • Emergency parachute system, and air-bag system (Cirrus SR20/22 safety features) Source (3)

  20. Preliminary Sizing and Synthesis - Weight • Weight Breakdown • Structure 85% Composites: • Wing • Tail • Fuselage • Emergency parachute system, and air-bag system (Cirrus SR20/22 safety features) Final WE = 1,497 Final TOGW = 2,443 Source (3, 4)

  21. Preliminary Sizing and Synthesis - Propulsion • 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 - Propulsion • Propulsion and Powerplant • Thrust vs. Altitude curves for varying Mach number Mach #: 0.28 0.24 0.20 0.16 0.12 0.08 0.04 0.00 Altitude (ft) Standard Day Thrust (lbs)

  23. Preliminary Sizing and Synthesis - Propulsion • Propulsion and Powerplant • Fuel consumption curves Mach #: 0.00 0.04 0.08 0.12 0.16 0.20 0.24 0.28 Altitude (ft) Standard Day SFC (lbsm/lbs hour )

  24. Preliminary Sizing and Synthesis - Aerodynamics • 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 - Aerodynamics • Aerodynamics • Drag polar for varying Mach number (graph) Mach = 0.2 Mach = 0.3 Mach = 0.4 Mach = 0.5 CD CL

  26. Preliminary Sizing and Synthesis - Mission 10,000 ft Altitude Cruise @ 200mph 45 min Loiter • Mission Performance: • Mission profile (schematic) 700 Miles Land @ SL, Standard TO @ SL, Standard 17.6 Gallons 39.7 mpg 700 miles (608.3 nm)

  27. Preliminary Sizing and Synthesis - Mission • Mission Performance: • Instantaneous cruise data:

  28. Preliminary Sizing and Synthesis – Constraint 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

  29. Preliminary Sizing and Synthesis – Constraint 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? Exceeded Exceeded Exceeded Exceeded Not Met

  30. Conclusions

  31. Conclusions • 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: • (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

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