The document presents the design of a new short take-off and landing (STOL) cargo aircraft. It outlines the mission requirements of a maximum take-off distance of 1,500 feet and a payload capacity of 1,775 pounds with a range of 800 nautical miles. The preliminary aircraft design includes a high-wing configuration with a turboprop engine providing over 1,000 horsepower. Performance analyses show the designed take-off distance is 1,146 feet, meeting requirements, and its calculated range is 830 nautical miles, exceeding the minimum. A cost estimation for building 500 aircraft over 5 years puts the price at around $1.77 million per plane, competitive with comparable aircraft.

1. Zenghui Liu, Frank Meyer, Keegan Smith

2. Background, Requirements, Mission Profile
3D Model
Interior Layout
Load, Weight Distribution and Structure
Wing Design
Propulsion
Performance
Stability and Control
Risk Analysis
Cost Estimation
Competitive Comparison

3.  Need for STOL Cargo Aircraft
Quest Kodiak Cessna 208

4. • Take-Off Distance: 1500 ft.
• Must clear 50 ft. obstacle at end of runway
• Weight of payload and crew: 1775 lbs.
• Range: 800NM

5.  Minimum range of 800 miles at max weight
400 mi

6. Mission Destination
Cruise Altitude = 25,000 ft

7. Background, Mission Profile, Requirements
Preliminary Design, 3D Model
Interior Layout
Load, Weight Distribution and Structure
Wing Design
Propulsion
Performance
Stability and Control
Risk Analysis
Cost Estimation
Competitive Comparison

8.  Tractor Configuration
 High Braced Wing
 Rectangular Wings
 Triangular Fixed Landing Gear

12. Mission Profile, Requirements
3D Model
Interior Layout
Load, Weight Distribution and Structure
Wing Design
Propulsion
Performance
Stability and Control
Risk Analysis
Cost Estimation
Competitive Comparison

13. 397 in.
(33.1 ft.)

14. Mission Profile, Requirements
3D Model
Interior Layout
Load, Weight Distribution and Structure
Wing Design
Propulsion
Performance
Stability and Control
Risk Analysis
Cost Estimation
Competitive Comparison

15.  NACA 4418
 NACA 2418
 NACA 23021
 NACA 1410
Airfoils found using
Theory of Wing Sections
by Abbott and Doenhoff

17. S (ft2
) 286
Chord (ft) 5.98
Span (ft) 47.8 Sv (ft2
) 26.3
Chord0 (ft) 4.3
Chordt (ft) 2.4
Span (ft) 6.5
Λ.25 0.35
St (ft2
) 50.1
Chord (ft) 2.9
Span (ft) 17.3
Wing
Tail
Vertical Tail

18. Aileronsflaps
• Flaps: 10-60% span, 25% chord
• Aileron: 60-90% span, 25% chord
• Elevator: 5-90% span, 35% chord
• Rudder: 5-90% span, 35% chord
Elevator

19. Mission Profile, Requirements
3D Model
Interior Layout
Load, Weight Distribution and Structure
Wing Design
Propulsion
Performance
Stability and Control
Risk Analysis
Cost Estimation
Competitive Comparison

20.  Power Required: 889 horsepower
 After Propeller Efficiency: 1000 horsepower
 Turboprop:
◦ More reliable
◦ Better efficiency at high altitudes
◦ Provides greater power to weight ratio when
compared to piston prop

23. Mission Profile, Requirements
3D Model
Interior Layout
Load, Weight Distribution and Structure
Wing Design
Propulsion
Performance
Stability and Control
Risk Analysis
Cost Estimation
Competitive Comparison

24. SG (ft) 531.6
SR (ft) 121.5
Stransition (ft) 493.1
Total (ft) 1146.2
Take-Off Distance Range
Required Take-Off Distance: 1500 ft.
Calculated Take-Off Distance: 1146 ft.
• Required Range: 800 NM
• Calculated Range from Breguet
equation: 830 NM

25. Mission Profile, Requirements
3D Model
Interior Layout
Wing Design
Propulsion
Performance
Weight Distribution, Center of Gravity
Stability and Control
Risk Analysis
Cost Estimation
Competitive Comparison

26. Component Weight (lbs) Location (ft) Moment (in-lb)
Wing 737 11.4 8393
Horizontal Tail 96 30.9 2971
Vertical Tail 83 31.9 2643
Fuselage 1048 16.5 17333
Main Landing Ger 416 14.0 5822
Nose Landing Gear 118 3.1 365
Installed Engine 653 3.1 2026
Fuel System 115 5.6 646
Flight Controls 153 16.5 2530
Hydraulics 0.20 16.5 3
Electrical 314 16.5 5188
Avionics 433 5.3 2297
Pilot/Crew 350 8.6 3004
Cargo/Passengers 1600 19.2 30667
Fuel 1818 9 16365
Furnishings 64 8.6 549
Totals 7997 12.6 100802

27. Wing 9%
Horizontal Tail 1%
Vertical Tail 1%
Fuselage 13%
Main Landing Gear 5%
Nose Landing Gear
1%
Installed Engine 8%
Fuel System 1%
Flight Controls 2%
Hydraulics 0%
Electrical 4%
Avionics 5%
Pilot/Crew 4%
Cargo/Passengers
20%
Fuel 23%
Furnishings 1%

28. Mission Profile, Requirements
3D Model
Interior Layout
Load, Weight Distribution and Structure
Wing Design
Propulsion
Performance
Stability and Control
Risk Analysis
Cost Estimation
Competitive Comparison

30. Phugoid Motion
Short-Period Motion
Damping Ratio: 0.68
Period: 0.29 seconds
Time to Half: 0.3 seconds
Damping Ratio: 0.09
Period: 7 seconds
Time to Half: 72 seconds

31. Mission Profile, Requirements
3D Model
Interior Layout
Load, Weight Distribution and Structure
Wing Design
Propulsion
Performance
Stability and Control
Risk Analysis
Cost Estimation
Competitive Comparison

33. Mission Profile, Requirements
3D Model
Interior Layout
Load, Weight Distribution and Structure
Wing Design
Propulsion
Performance
Stability and Control
Risk Analysis
Cost Estimation
Competitive Comparison

34. **The cost estimation is based on total quality of 500
aircrafts in 5 years
Engineering Hours HE $574,265.63
Tooling Hours HT $466,237.46
Manufacturing Hours HM $2,829,233.94
Quality Control Hours HQ $225,772.87
Development Support CD $9,665,131.61
Flight Test CF $3,903,783.37
Manufacturing Materials CM $107,998,634.49
Engineering Production Ceng $733,916.93
RDT&E + flyaway $885,856,482.73
Each Aircraft $1,771,712.97

35. Mission Profile, Requirements
3D Model
Interior Layout
Load, Weight Distribution and Structure
Wing Design
Propulsion
Performance
Stability and Control
Risk Analysis
Cost Estimation
Competitive Comparison

36.  Pricing:
◦ Kodiak: $1.7 million
◦ Cessna 208: $2.02 million
◦ HSA Aircraft: $1.77 million
 Payload Capacity (max fuel):
◦ Kodiak: 733 lbs.
◦ Cessna: 2324 lbs.
◦ HSA Aircraft: 1775 lbs.
 Take-Off Distance:
◦ Cessna: 2420 ft. (sea level)
◦ Kodiak: 1181 ft. (sea level)
◦ HSA Aircraft: 1146 ft. (5000 ft. elevation)