1. Group 3 Heavy Lift Cargo Plane
William Gerboth, Jonathan Landis, Scott Munro, Harold Pahlck November 12, 2009

2. Presentation Outline Project Objectives Final Conceptual Design
Q&A From Phase I
Technical Analysis Approach
Technical Analysis
Plan For Phase III
Nugget Chart

3. Project Objectives
Design and build an airplane to successfully compete in the SAE Aero East competition
Plane must successfully take off from a runway of 200 feet and land on a runway 400 feet
Constraints of 55 pounds total weight, and the combined height, length, and width of 200 inches
Plane must make one complete 360° circuit of the field per attempt

4. Conceptual Designs
From our concept matrices we chose the designs that scored the highest, the final design concepts are as follows
Airfoil Shape: Eppler 423
Wing Shape: Straight
Landing Gear: Tricycle
Tail shape: T-Tail

5. Q&A from phase I Competition Scoring:
The total score is the flight score + Design Report+ Oral presentation
FS=RAW+PPB+EWB-TP
RAW=Raw weight score=Wx4 (W=weight lifted in LBs)
PPB= Prediction point bonus= 20-(PP-PA)2 (Pp=predicted payload, PA =actual payload
EWB=empty payload bonus (10 point for a successful empty flight)
TP= total penalties (From design report, technical inspection, Aircraft modifications)
Design report is out of 50 points

6. Q&A from phase I (cont.) Plan For victory in completion
Control of the Plane
A 2.4GHz radio controller will be used (competition rules)
Flaps, Ailerons, Rudder, Elevators, and Throttle will be moved by servos controlled by radio

7. Technical Analysis Approach
Perform Calculations for:
Drag
Lift
Velocity
Take off distance (>200 ft.)
Landing distance (>400ft.)

8. Technical Analysis: Friction Drag
Assumptions
Altitude 3000 ft.
ρ = slugs/ft3
µ = x10-6 slugs/ft – sec
Friction drag depends on velocity so it must be calculated for takeoff, landing, and cruising

9. Technical Analysis: Drag (Fuselage)

10. Technical Analysis: Drag (Wing)

11. Technical Analysis: Drag (Horizontal Tail)

12. Technical Analysis: Drag (Vertical Tail)

13. Technical Analysis: Drag (Tail Boom)

14. Technical Analysis: Drag (landing gear and engine)

15. Technical Analysis: Total Friction Drag

16. Technical Analysis: Profile Drag (Fuselage & Landing Gear)

17. Technical Analysis: Profile & Induced Drag (wing at cruise)

18. Technical Analysis: Profile & Induced Drag (wing landing)

19. Technical Analysis: Profile & Induced Drag (wing takeoff)

20. Technical Analysis: Total Drag

21. Technical Analysis: Flaps and Aileron
Length
Ailerons = 35-40% of span  .38*57.5 = 35.65
Flaps = % of span  .62*57.5 = 21.85
Width
25% of chord
Aileron width  3 in.
Flap width  3 in.
Span
Flap
Aileron C
.25C
35-40%
60-65%
100%

22. Technical Analysis: Velocity Flaps fully down at 40 deg.
Stall Velocity
=24.18 mph
=35.47 ft/s
Takeoff Velocity
=29.02 mph
=42.56 ft/s
Landing Approach Velocity
=31.44 mph
=46.11 ft/s
Cruise Velocity
=35.07 mph
=51.43 ft/s

23. Technical Analysis: Landing CL
=2.5659
Takeoff Velocity
=915.13 =
=2.160

24. Technical Analysis: Lift Calculation At .7Vto
T = Static Thrust Available =
Fc = Coefficient of Rolling Friction = 0.035
=17.105
=6.684
= ft
With a 25% safety factor =

25. Technical Analysis: Landing Calculation At .7Vl
W = 35 lb. = 560 oz.
Fc = Coefficient of Rolling Friction = 0.035
=24.47
=376.67

26. Plan for Phase III Complete Final Design Create CAD models of Aircraft
Use CAD models to analyze final Aircraft design

27. ME 423 Phase II Nugget Chart – Design Selection and Technical Analysis
Title: Heavy Cargo Lift Plane Team Members: William Gerboth, Scott Munro, Jonathan Landis, Harold Pahlck Advisor: Professor Siva Thangam Project #: Date: 11/12/09
Project Objectives
Design and build an airplane that conforms to the SAE competition rules and regulations.
Plane must navigate a 360 degree after taking off from within a 200 foot runway, and then land successfully on a runway of 400 feet.
Constraints of 55 total pounds and a height, width, and length of 200 inches must be followed.
Results Obtained at This Point
Types and Focuses of Technical Analysis
Force analysis of structural members of wing, tail, and fuselage.
Stress analysis of materials to use for structural members
Deflection tests of landing gear
Static analysis for wing and tail design
Aerodynamic analysis to maximize lift and minimize drag
Propeller design to maximize the power available in the engine
Drawing and Illustration (about technical analysis performed)
Design Specifications
Wing span of 120 inches
Overall length of 68 inches
Height of 12 inches
Thrust of pounds
Estimated payload of 23 pounds
Plane weight of 12 pounds