1. 2007 SAE Heavy Lift Cargo Plane
December 14, 2007
2007 SAE Heavy Lift Cargo Plane
Ducks on a Plane
Joe Lojek Justin Sommer
James Koryan Ramy Ghaly
Advisor: Professor Siva Thangam

2. Introduction 2007 SAE Aero East Rules & Regulations
Design Influences & Final Concepts
Bill of Basic Materials & Transportation
Design Selection and Justification
Calculations
Team Dynamics
Conclusion

3. 2007 SAE Aero East Rules and Regulations
Regular Class
1000 sq in max platform area
200 ft take-off
400 ft landing
Cannot modify engine gear ratio
Take off into headwind
360° Aerial Circle
No “showboating”
Competition Date
May 4nd-6th Fort Worth, TX

4. Design Influences & Final Concepts
Previous Completion Designs
Commercial Cargo Planes (C-17)
Final Concepts
Wing design
Landing Gear
Tail Design
Fuselage

5. Basic Materials Balsa Wood Aluminum (1060) Carbon fiber Tubing
Wings
Flaps
Fuselage
Tail
Aluminum (1060)
Landing Gear
Carbon fiber Tubing
Wing Reinforcement
Thermal Mono-coat Shelling
Wing
Resin
Engine Cap
¼” Plywood
Fuselage Framing
Item
Qty.
Cost/Unit
Cost
Servos 4
$25.00
$100.00
Balsa Wood
Wheels 3"
$5.00
$20.00
6V 3700mAh NiMH Battery Module 1
$18.95
Servo Extension wires
$9.00
$36.00
Sandpaper Grit assortment
$15.00
Epoxy
$3.50
Wood Glue
Servo Arm Standard Assortment 2
$3.95
$7.90
X-Acto Basic Knife Set
$24.00
Propeller 11x6-13x6 6
$13.95
Plywood 8x4x1/8
Carbon fiber tubing
$15.70
$31.40
Spinner
$10.00
O.S. FX61 Engine
$159.99
Motor Mount
$17.00
Total 30
$204.55
$501.19

6. Transportation Driving Qty Cost Food (25/day*member)) 7 $100.00
$700.00
Week Cargo Van Rental 1
$534.32
2007 IRS Standard Mileage Rate
$0.49
$1,532.01
Hotel (2 Rooms) 3
$150.00
$450.00
Hourly Rate (35.5/hr) 48
$142.00
$6,816.00
Total Cost
$9,332.33
Flying
Qty
Cost
Round Trip Newark, NJ -Fort Worth, TX 4
$271.00
$1,084.00
Hotel (2 Rooms) 3
$150.00
$450.00
Daily Rent for Cargo Van
$60.00
$180.00
2ND Day UPS Shipment (50lb) Freight 1
$408.00
Packaging Cost
$100.00
Food (25/day*member)
$400.00
Hourly Rate (35.5/hr) 12
$142.00
$1,704.00
Total Cost
$4,326.00

7. Design and Calculations

8. Monoplane Mono-Plan Advantages Disadvantages Less Drag
Ease of Construction
Lightest Design
Best Maneuverability
Disadvantages
Less Stability
Lower Levels of Lift

9. Eppler 423
Eppler 423 was chosen
Highest lift coefficient

10. Conceptual Airfoil Design
Advantages
Highest Lift
Stable
Ease of construction
Disadvantages
High Drag
High Pitch Moment

11. Wing Shape Wing Shapes Elliptical Swept Tapered Advantages
Decreased Drag
Increased Stability
Increased Maneuverability

12. Conceptual Design: T-Tail
Advantages
Ideal for Low Speed
Flow over tail
unaffected from wing flow
Disadvantages
Prone to Deep Stall
Tend to be heavier

13. Horizontal Tail Plane NACA 0009 Symmetrical airfoil profile 0 Camber
Very low drag
CL of 0.8

14. Pitching Moment Calculations
lbs/in
+/-, Nose up/Nose Down
Assumption-
The CG is vertically inline with
the wings aerodynamic center.
Pitching Moment = (CM * s * V2 * S * C) / 3519
CM - Pitching moment coefficient
S - (density of sea level : 1
S - wing area
V - speed in mph

15. Tail Plane Calculations
Horizontal Tail
TMA = (2.5 * MAC * 0.20 * WA) / HTA
TMA – Tail moment arm, inches
HTA – Horizontal tail area, in2
WA – Wing area, in2
MAC – Mean aerodynamic chord, in
Downward force needed
/ = 4.05lbs
Horizontal tail plane dimensions
Chord: 5 in
Span: 24 in  120in2
Lift = (CL * s * V2 * S) / 3519 = 4.26 lbs

16. Conceptual Landing Gear Design
1060 Aluminum.
Tricycle design
more secure landing with a heavier weight.
with 3 wheels, each 4 inches in diameter and ½ inch wide,
Cd= 3(1.01)(2) /1440 = .0042

17. Landing Gear Factor of Safety (4.2)

18. Reynolds number (Re) Re = Fn(ρ,V,µ,x),
where x is each parts reference length
For laminar flow,
For transitional flow,
For turbulent flow,

19. Wing Calculations
 Laminar Flow!!!

20. Fuselage Calculations
 Turbulent Flow!!!

21. Horizontal/Vertical Tail Calculations
 Laminar Flow!!!

22. Thrust Calculations
During takeoff, at a takeoff velocity of ft/s,
Thrust = lb

23. Flaps Calculations Lift = 63 lbf
From the RC handbook and Professor Thangam,
Where,
a= angle of attack = .227 radians
Β= angle of deflection = .209 radians
c= max camber= .0992
Lift = 63 lbf

24. Final Design

25. Team Dynamics Organizational Skills Time Management
Communication Skills
Cultural Barriers
Work Habits and Efficiency

26. Conclusion Monoplane Wing Design Tail Design Materials to be Used
Eppler 423
Swept & Tapered Wing
Tail Design
NACA 0009
T-Tail Design
Materials to be Used
Landing Gear
1060 Aluminum
Tripod Setup
Transportation
Air travel most time and cost efficient