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

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 Purdue University AAE 451 Senior Design Team 1

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 Purdue University AAE 451 Senior Design Team 1

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 Purdue University AAE 451 Senior Design Team 1

Design Concept Purdue University AAE 451 Senior Design Team 1

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

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% Purdue University AAE 451 Senior Design Team 1

Carpet Plot Design Points Summary Constraint Analysis Carpet Plot Design Points Summary AR W/S P/W T/W GTOW 8 31.3 0.091 0.3140392 11360 9 0.0875 0.3019608 11317 10 0.086 0.2967843 11343 11 11448 Purdue University AAE 451 Senior Design Team 1

Compliance with Design Requirements Goal Threshold Value Payload (lbs) 2000 ≥ 1500 Range (nm) 1200 ≥ 900 TO Field Length (ft) ≤ 2000 ≤ 5000 3295 TOGW (lbs) ≤ 12,500 12,432 Max Speed (knots) ≥ 250 ≥ 184 241 Acq. Cost ($US2006 millions) ≤ $2.5 ≤ $3.5 $3.24 DOC ($US2006) ≤ $500/hr $424/hr Purdue University AAE 451 Senior Design Team 1

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

Structure - Fuselage Forward Section used for main payload/passengers 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 Purdue University AAE 451 Senior Design Team 1

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 Purdue University AAE 451 Senior Design Team 1

Structural Material Selection Aircraft Section Material Selection Yield Strength Approximate Cost Advantages Disadvantages Wing/Tail Structure (Spars, ribs, stringers) Aluminum Alloy 7075 or 7150 ~70,000 psi $4.00 – 5.00/lb Strength, resists corrosion. commonly used, low cost Fatigue life Fuselage (Keel beams, ribs, longerons) Alloy 6061 or 7075 Wing/tail Skin & Fuselage skin Alloy 2090-T83 ~77,000 psi Up to $10.00/lb Very high strength, resist corrosion, weight reduction relatively new material, more expensive Landing gear 2024-T6 60,000 – 70,000 psi $3.00/lb Strength, resists corrosion. commonly used, cheap Purdue University AAE 451 Senior Design Team 1

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 Purdue University AAE 451 Senior Design Team 1

Drag Polar Purdue University AAE 451 Senior Design Team 1

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

Stability AC of wing CG location Neutral Point AC of Vertical Tail AC of Horizontal Tail Purdue University AAE 451 Senior Design Team 1

Stability Static Margin (SM): 16.1% Neutral Point: 19.6 ft Wing Aerodynamic Center 15.0 ft Leading Edge location 13.3 ft Trailing Edge location 20.0 ft Static Margin (SM): 16.1% Neutral Point: 19.6 ft Vertical Tail Horizontal Tail distance from AC of v-tail to AC of wing 32 ft distance from AC of h-tail to AC of wing 34 ft v-tail volume coefficient 0.0665 h-tail volume coefficient 0.69 Area of vertical tail 49.4 ft2 Area of horizontal tail 53.5 ft2 Purdue University AAE 451 Senior Design Team 1

Performance Optimal Performance Values V-n Diagram Parameter Value Units Vcruise 170 knots Vstall 61 Vmaxgliderange 148 γmaxclimb 15.3 deg Climb ratemax 46 ft/s gust normal Purdue University AAE 451 Senior Design Team 1

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

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) Purdue University AAE 451 Senior Design Team 1

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 Purdue University AAE 451 Senior Design Team 1

Cost Acquisition cost DOC Our Aircraft: Grand Caravan: PC-12: $3.24 million $1.75 million $3.4 million RDT&E: $415 million $226 million $421 million Flyaway Cost: $1.17 million $618,000.00 $1.3 million Our Aircraft: Grand Caravan: PC-12: DOC ($/hr): $424.64 $332.95 $370.00 Purdue University AAE 451 Senior Design Team 1

Conclusion Will concept be successful? Significant “open” issues 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 Purdue University AAE 451 Senior Design Team 1

Questions? Purdue University AAE 451 Senior Design Team 1

Acquisition Cost Breakdown: Power series function Depends on wing span, AR, GTOW, thrust, cruise speed, and range ln(cost)= {constants}*{vector of ln(parameters)} Real Cost: Our Cost Model: Caravan 675 $1.8 million $1.9 million Beech King Air C90GT $2.95 million $2.86 million Beech 1900D $5.4 million $5.59 million Avanti II $6 million $6.1 million Purdue University AAE 451 Senior Design Team 1

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) Purdue University AAE 451 Senior Design Team 1

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 Purdue University AAE 451 Senior Design Team 1

Cost Assumptions: RDT&E and Flyaway Costs: DOC: 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 Purdue University AAE 451 Senior Design Team 1

Constraint Analysis Purdue University AAE 451 Senior Design Team 1

Sizing Method FLOPS Input parameters Calibration 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% Purdue University AAE 451 Senior Design Team 1