1. 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

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
Purdue University
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: 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

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
Purdue University
AAE 451 Senior Design Team 1

5. Design Concept
Purdue University
AAE 451 Senior Design Team 1

6. Concept Configurations1 4 2
10 seats
Executive
Combination seats/shipping container
3 shipping containers (LD-3 Standard) 3
Purdue University
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%
Purdue University
AAE 451 Senior Design Team 1

8. 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
11360 9
0.0875
11317 10
0.086
11343 11
11448
Purdue University
AAE 451 Senior Design Team 1

9. 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

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

11. 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

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 = feet
Wheelbase = 17 feet
Purdue University
AAE 451 Senior Design Team 1

13. 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

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

15. Drag Polar
Purdue University
AAE 451 Senior Design Team 1

16. 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

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

18. 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

19. 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

20. Performance Operating Envelope Constant energy heights Stall limit
Ps=0
q limit
Cruise Height
Purdue University
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: lb/hp/h)
Purdue University
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
Purdue University
AAE 451 Senior Design Team 1

23. 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

24. 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

25. Questions?
Purdue University
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)}
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

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)
Purdue University
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
Purdue University
AAE 451 Senior Design Team 1

29. 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

30. Constraint Analysis
Purdue University
AAE 451 Senior Design Team 1

31. 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