1. 1 AAE 451 Senior Aircraft Design Spring 2006 Preliminary Design Review Group VI Team Members: John Collins Chad Davis Chris Fles Danny Sze Ling Lim Justin Rohde Ryan Schulz Ronald Wong Yusaku Yamashita

2. 2 Market Review Target: Business Market Target: Business Market Corporate Flight DepartmentsCorporate Flight Departments Air Taxi and Air CharterAir Taxi and Air Charter Fractional SharesFractional Shares Profit Opportunities Profit Opportunities Air taxi, fractional ownership expected to more than double in coming decadeAir taxi, fractional ownership expected to more than double in coming decade Increasing incentive for use by small businessIncreasing incentive for use by small business Strong business aviation growth expected in European and Asian markets over next 20 yearsStrong business aviation growth expected in European and Asian markets over next 20 years

3. 3 Design Requirements Cabin Capacity - 2 Crew + 6 Passengers Cabin Capacity - 2 Crew + 6 Passengers Cruise Range - 600 nm Cruise Range - 600 nm Cruise Speed - 250 kts Cruise Speed - 250 kts T.O./Landing Distance - 2,100 ft T.O./Landing Distance - 2,100 ft Acquisition Cost - $1.8 Million Acquisition Cost - $1.8 Million D.O.C./Hour - $550 D.O.C./Hour - $550 Taxi Take-off 2100 ft. Runway Climb Cruise Descend for Landing 600 nm rangeReserve Execute Missed LandingLand 2100 ft. Runway Begin Landing Pilots (150 lbs. each) Pilots (150 lbs. each) Passengers (200 lbs. each) Passengers (200 lbs. each) 1500 lbs. Total Payload 1500 lbs. Total Payload 200 nm cruise + 45 min loiter V-cruise = 250 kts @ 20,500 ft

4. 4 Present Concept

5. 5 Sizing Major parameters Major parameters P/W = 0.1716 hp/lbP/W = 0.1716 hp/lb W/S = 32 lb/ftW/S = 32 lb/ft AR = 7.6AR = 7.6 TOGW = 6500 lbTOGW = 6500 lb λ = 0.4λ = 0.4 Costs Costs Acquisition = $1.725 MillionAcquisition = $1.725 Million Direct Operating = $450/HourDirect Operating = $450/Hour Carpet Plot Approach Carpet Plot Approach We/Wo – Regression:We/Wo – Regression: P/W, W/S, AR, V-max, TOGWP/W, W/S, AR, V-max, TOGW We/Wo – Verified:We/Wo – Verified: Component Weight AnalysisComponent Weight Analysis

6. 6 Concept Comparison Concept 15 Socata TBM 700 [i] [i] Pilatus PC 12 [ii] [ii] TOGW 6500 lb6578 lb9920 lb W/S 32 lb/ft²33.9 lb/ft²35.7 lb/ft² Wing Area 212 ft 2 193.8 ft 2 277.8 ft 2 AR 7.68.979.85 Wing Span 40 ft41ft 7 in52 ft 3 in P/W 0.1716 0.1060.121 S TO 2100 ft2133 ft2300 ft V Cruise 250 kts243 kts232 kts Acquisition Cost $1.725 M$ 2 M$ 2.8 M D.O.C. $450/hr$425/hr$400/hr RequirementsConcept 15 Capacity 2 Crew 6 Passengers 2 Crew 6 Passengers Range 600 nm w/ 200 nm divert 45 min loiter Cruise Speed 250 kts Vbest = 225 kts Vmax = 265 kts Acquisition Cost $1.8 M$1.725 D.O.C. $550/Hour$450/Hour

7. 7 Aerodynamics Wing Airfoil Selection Criteria Wing Airfoil Selection Criteria High C lmax (Required C lmax =1.5)High C lmax (Required C lmax =1.5) High L/D(Required L/D = 11.66)High L/D(Required L/D = 11.66) Low C dLow C d Low C m.25 at cruiseLow C m.25 at cruise NACA 22012 was selected as it can meet the requirements at a lower drag penalty than NACA 4412NACA 22012 was selected as it can meet the requirements at a lower drag penalty than NACA 4412 20 degree deflection of plain flaps located at ¾-chord were used during takeoff to augment the C l required20 degree deflection of plain flaps located at ¾-chord were used during takeoff to augment the C l required Wing - NACA 22012 Take off with 20deg flaps Cruise CLCLCLCL1.6220.22 C m.25 -0.207-0.007

8. 8 Drag Polar C l – alpha curve with and without flaps

9. 9 Canard Airfoil Canard Airfoil NACA 2212 was selected as it provides adequate C L at cruise to meet the L/D requirement.NACA 2212 was selected as it provides adequate C L at cruise to meet the L/D requirement. Winglet Airfoil Winglet Airfoil NACA 4412 was selected based on Raymer’s textbook, “the camber of the winglet must be greater than that of the wing to ensure sufficient side force.”NACA 4412 was selected based on Raymer’s textbook, “the camber of the winglet must be greater than that of the wing to ensure sufficient side force.” Canard - NACA 2212 Take off Cruise ClClClCl0.4370.185 C m.25 -0.039-0.034 Aerodynamics – Wing Selection Winglet - NACA 4412 ClClClCl0.276 C m.25 -0.098

10. 10 Drag Estimation C d0 WingsCanardWingletsFuselage Take-off0.01770.00240.000720.00102 Cruise0.01540.00210.000620.0009 Fuselage Upsweep Landing Gears Misc. Drag 0.002580.0026 Total Parasite Drag Total Drag Take-off0.0360.148 Cruise0.0220.026 Note: Figures might not add up due to rounding error

11. 11 Summary of Aerodynamic Performance C Lmax = 1.622 C Lmax = 1.622 C Lcruise = 0.320 C Lcruise = 0.320 L/D = 12.26 L/D = 12.26 C d cruise = 0.026 C d cruise = 0.026 C d takeoff = 0.148 C d takeoff = 0.148

12. 12 V-n Diagram V stall = 68 kts V cruise = 250 kts V dive = 280 kts V AOA = 115.65 kts

13. 13 Structures Box Beam Analysis Program Box Beam Analysis Program Compares Different MaterialsCompares Different Materials Includes TolerancesIncludes Tolerances Deflection Deflection Buckling Buckling Shear Shear Program Minimizes Material UsedProgram Minimizes Material Used Loading Conditions Loading Conditions Trapezoidal Lift DistributionTrapezoidal Lift Distribution Large Bending Moment at Wing RootLarge Bending Moment at Wing Root Lateral Forces Applied on WingletLateral Forces Applied on Winglet

14. 14 Structures Results Results Aluminum CompositeAluminum Composite 140 lb Supporting Structure / Wing 140 lb Supporting Structure / Wing AluminumAluminum 170 lb Supporting Structure / Wing 170 lb Supporting Structure / Wing Loading Factor – 2.0 Before FailureLoading Factor – 2.0 Before Failure Further Optimization RequiredFurther Optimization Required

15. 15 Component Weight Breakdown (Numbers) Components Weight (lb) Wing400.00 Canard150.15 Winglets70.00 Fuselage168.87 Landing gearNose31.27 Main184.67 Installed Engine800.00 All else1536.70 Total Empty Weight3321.66 Components Weight (lb) Total Empty Weight3321.66 Fuel1665 Crew (pilot + copilot)300 Passengers (6 PAX)1200 Gross Takeoff Weight (GTOW) 6486.66

16. 16 Component Weight Breakdown (empty) Total Empty Weight = 3321.6 lb

17. 17 Component Weight Breakdown (Gross takeoff Configuration) Gross Takeoff Weight = 6500 lb

18. 18 Component Weight Distribution

19. 19 CG Travel and Static Margin CG Travel and Static Margin

20. 20 Propulsion Cruise SFC – 0.553 Cruise SFC – 0.553 Installed Power – 1000 hp Installed Power – 1000 hp Similar Engine - PT6A-60A Similar Engine - PT6A-60A Propeller Propeller Diameter - 8 ftDiameter - 8 ft 4 Blades4 Blades η p Max Speed – 0.91η p Max Speed – 0.91 Variable PitchVariable Pitch Feathering and Reversible Feathering and Reversible PT6A – Large – www.unitedtubrine.com

21. 21 Propulsion Considerations

22. 22 Fuel Considerations BioJet Fuel BioJet Fuel First Created by University of North DakotaFirst Created by University of North Dakota Heating Value – 16,000 (btu/lb)Heating Value – 16,000 (btu/lb) Specific Gravity – 0.87-0.89Specific Gravity – 0.87-0.89 TSFC – 0.553 *ApproximateTSFC – 0.553 *Approximate Compatible with Current TurbinesCompatible with Current Turbines Engine Heat Used to Prevent GellingEngine Heat Used to Prevent Gelling

23. 23 Cost Acquisition Acquisition $1.725 Million$1.725 Million Regression of Similar AircraftRegression of Similar Aircraft Based on:Based on: Gross Weight Gross Weight Aircraft Performance Aircraft Performance DOC DOC $450 / Hour$450 / Hour Component AnalysisComponent Analysis

24. 24 Competing Aircraft Acquisition Cost Acquisition Cost Baron G58 - $1.22 MBaron G58 - $1.22 M Adam A500 - $1.25 MAdam A500 - $1.25 M Pilatus PC-12 - $2.80 MPilatus PC-12 - $2.80 M Concept 15 - $1.725Concept 15 - $1.725 D.O.C./Hour D.O.C./Hour Baron G58 - $288 Adam A500 - $450 Pilatus PC-12 - $400 Concept 15 - $450

25. 25 Production Costs Recurring Costs Manufacturing Materials Quality Control Development Support Engines Avionics Inventory Non-Recurring Costs Engineering/Design Tooling Flight Testing DAPCA model (Raymer) used to estimate costs - Adjusted to current dollar value - Weighting used for composite components - Learning curve applied to various recurring man-hours as production progresses

26. 26 Production Costs Significant decrease in unit cost as production increases Acquisition cost of $1.725M; includes 30% profit Break even point ~ 210 aircraft

27. 27 Production Cost Breakdown Engineering, development, and testing decrease substantially in percentage as production increases Manufacturing, materials costs begin to level off

28. 28 Production Cost Breakdown

29. 29 Summary Concept 15 Concept 15 Design Requirements AchievedDesign Requirements Achieved Mission Requirements Met Mission Requirements Met Stable Aircraft (Positive Static Margin) Stable Aircraft (Positive Static Margin) Aerodynamic Properties Possible Aerodynamic Properties Possible Need Wind Tunnel Verification (Better Approximations)Need Wind Tunnel Verification (Better Approximations) Competitive Cost Achieved Competitive Cost Achieved

30. 30Questions