AAE 451 Senior Aircraft Design Spring 2006 Preliminary Design Review Group VI

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

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

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

4. Present Concept

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

6. Concept Comparison

7. Aerodynamics • Wing Airfoil Selection Criteria • High Clmax (Required Clmax=1.5) • High L/D (Required L/D = 11.66) • Low Cd • Low Cm.25 at cruise • NACA 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 Cl required

8. Drag Polar Cl – alpha curve with and without flaps

9. Aerodynamics – Wing Selection • Canard Airfoil • NACA 2212 was selected as it provides adequate CL at cruise to meet the L/D requirement. • 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.”

10. Drag Estimation Note: Figures might not add up due to rounding error

11. Summary of Aerodynamic Performance • CLmax = 1.622 • CLcruise = 0.320 • L/D = 12.26 • Cd cruise = 0.026 • Cd takeoff = 0.148

12. V-n Diagram Vstall = 68 kts Vcruise = 250 kts Vdive = 280 kts VAOA = 115.65 kts

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

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

15. Component Weight Breakdown (Numbers)

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

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

18. Component Weight Distribution

19. CG Travel and Static Margin

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

21. Propulsion Considerations

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

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

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

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

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

28. Production Cost Breakdown

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

30. Questions