Preliminary Design Review

1. Preliminary Design Review Miguel Alanis Aaron Mayne Tim Block Jason Olmstead Becca Dale Adeel Soyfoo Joseph Fallon Sarah Weise AAE 451 Senior Design Team 1

2. Review of Concept and Market • Multi-functional, Rugged, Non- petroleum fueled Airplane to serve: • Air charters, governments (surveying, mail), medical transport, or supplies delivery companies • Operates in rural, developing areas of the world such as Australia, South America, or even rural parts of Canada AAE 451 Senior Design Team 1

3. Design Requirements • Payload: • 2000 lbs, or • 10 passengers • Range: 1200 nm • One-way full load • Takeoff Field Length: 2000 ft • Service ceiling: 25000 ft • Max speed: 250 kn • Weight: ≤ 12,500 lbs • Acquisition Cost: < $2.5 million • Alternate Fuel Source AAE 451 Senior Design Team 1

4. Design Concept • Main Features: • Tapered Wing • High Wing with Strut Support • T-Tail • Non Pressurized Cabin • Fixed Landing Gear • 66” Cargo Door • 4 ft Ground Clearance AAE 451 Senior Design Team 1

5. Design Concept AAE 451 Senior Design Team 1

6. Concept Configurations 1 4 2 • 10 seats • Executive • Combination seats/shipping container • 3 shipping containers (LD-3 Standard) 3 AAE 451 Senior Design Team 1

7. Sizing of Aircraft • TOGW: 12,432 lbs • W/S: 31.3 lb/ft2 • P/W: 0.0875 • AR: 9 • λ = 0.3 • Acquisition cost: $3.24 million • Operating cost: $424.64/hr • Sizing done using FLOPS Flight Optimization System, Release 6.11(internal cost model not used) • Calibrated Using Cessna Grand Caravan • TOGW error ≈ 2% AAE 451 Senior Design Team 1

8. Constraint Analysis AAE 451 Senior Design Team 1

9. Compliance with Design Requirements AAE 451 Senior Design Team 1

10. Structure - Wing and Tail Main and Rear Spar Rib Members Stringers Fuel tanks AAE 451 Senior Design Team 1

11. Structure - Fuselage Length = 38 ft • Forward Section used for main payload/passengers • Aft Section for stability purposes • 2 main keel beams running longitudinally in forward section, used to support heavy payload • 12 transverse square ribs/frames along fuselage length • 16 longitudinal stringers/longerons AAE 451 Senior Design Team 1

12. Structure - Landing Gear • Non-retractable • Tricycle Layout • 2024-T6 Aluminum • Need to carefully choose specific tires (depends on type of runway landing) 50.76 deg Tread = 10.54 feet Wheelbase = 17 feet AAE 451 Senior Design Team 1

13. Structural Material Selection AAE 451 Senior Design Team 1

14. Aerodynamics • Airfoil NACA 4412 has the Highest cLmax • Slotted Flap on Entire Wing • CLcruse=0.4 • CL@L/Dmax =0.6 • CLmax=2.4 • Wing Area=400 ft2 • Taper Ratio=0.3 AAE 451 Senior Design Team 1

15. Drag Polar AAE 451 Senior Design Team 1

16. C.G. Location:18.5ft Weight Breakdown: Payload: 2000 lbs Crew: 410 lbs Empty Weight: 6,113 lbs Fuel Weigh: 3,903 lbs Weight & Balance Green loading plane, Blue unloading plane AAE 451 Senior Design Team 1

17. Stability • AC of wing • CG location • Neutral Point • AC of Vertical Tail • AC of Horizontal Tail AAE 451 Senior Design Team 1

18. Stability • Static Margin (SM): 16.1% • Neutral Point: 19.6 ft AAE 451 Senior Design Team 1

19. Performance • Optimal Performance Values • V-n Diagram gustnormal AAE 451 Senior Design Team 1

20. Performance • Operating Envelope Constant energy heights Stall limit Ps=0 q limit Cruise Height AAE 451 Senior Design Team 1

21. Engine • Pratt & Whitney Canada PT6A-67D • Delivers up to 1271 hp (1250 hp required) • High power to weight ratio • High reliability • Low fuel consumption (sfc at full power: 0.546 lb/hp/h) AAE 451 Senior Design Team 1

22. Propeller & Thrust produced • 4-bladed aluminum propeller • Integrated design lift coefficient cL = 0.500 • Activity factor 140 • Diameter 110 in • Rotational speed 1700 rpm • Blade Tip Speed Ma = 0.78 AAE 451 Senior Design Team 1

23. Cost • Acquisition cost • DOC AAE 451 Senior Design Team 1

24. Conclusion • Will concept be successful? • Feasible design • New concept will give market advantage • Derived versions could offer more cabin space but shorter range • Competition from remodeled petrol fueled aircraft • Significant “open” issues • Stall characteristics (T-tail) • Finalize wing design (flap size) • Improve Takeoff and Landing Performance • Develop Bio-fuel kit for PT6A turbine AAE 451 Senior Design Team 1

25. Questions? AAE 451 Senior Design Team 1

26. Acquisition Cost Breakdown: • Power series function • Depends on wing span, AR, GTOW, thrust, cruise speed, and range ln(cost)= {constants}*{vector of ln(parameters)} AAE 451 Senior Design Team 1

27. RDT&E and Flyaway Costs: • DAPCA model outlined in Raymer’s text • Did not give an accurate acquisition cost • Did give accurate percentages for the RDT&E and Flyaway cost break down RDT&E = 0.64*(Acquisition Cost) Flyaway = 0.36*(Acquisition Cost) AAE 451 Senior Design Team 1

28. DOC: • DAPCA model outlined in Raymer’s text • Did not give an accurate DOC, but calculated value was off by a consistent percentage • Calculated our DOC at current fuel prices • Adjust DOC according to: real DOC = 0.64*(calculated DOC)  • Added in addition costs due to increased fuel price AAE 451 Senior Design Team 1

29. Cost Assumptions: • RDT&E and Flyaway Costs: • 200 aircraft to break even • 2 flight test aircraft • Avionics are 7% of the flyaway cost • DOC: • 1000 FH/year • 1 MMH/FH • Properties of our fuel are the same as kerosene • Current fuel: $2.40 1/gal, FT: $7.40 1/gal AAE 451 Senior Design Team 1

30. Constraint Analysis AAE 451 Senior Design Team 1

31. Sizing • Method • FLOPS • Input parameters • T/W, converted from P/W with prop numbers • Geometric Characteristics • Mission and Performance Constraints • Engine Definition • Wing Definition • Calibration • Cessna Grand Caravan • TOGW error aprrox. 2% AAE 451 Senior Design Team 1