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

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

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

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

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

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

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

Technical Analysis: Friction Drag Assumptions Altitude 3000 ft. ρ = 0.002175 slugs/ft3 µ = 0.36677x10-6 slugs/ft – sec Friction drag depends on velocity so it must be calculated for takeoff, landing, and cruising

Technical Analysis: Drag (Fuselage)

Technical Analysis: Drag (Wing)

Technical Analysis: Drag (Horizontal Tail)

Technical Analysis: Drag (Vertical Tail)

Technical Analysis: Drag (Tail Boom)

Technical Analysis: Drag (landing gear and engine)

Technical Analysis: Total Friction Drag

Technical Analysis: Profile Drag (Fuselage & Landing Gear)

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

Technical Analysis: Profile & Induced Drag (wing landing)

Technical Analysis: Profile & Induced Drag (wing takeoff)

Technical Analysis: Total Drag

Technical Analysis: Flaps and Aileron Length Ailerons = 35-40% of span  .38*57.5 = 35.65 Flaps = 60 -65% 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%

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

Technical Analysis: Landing CL =2.5659 Takeoff Velocity =915.13 =2195.41 3110.547 =2.160

Technical Analysis: Lift Calculation At .7Vto T = Static Thrust Available = 11.865 Fc = Coefficient of Rolling Friction = 0.035 =17.105 =6.684 =135.52 ft With a 25% safety factor = 169.397

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

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

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 #: 3 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 11.86 pounds Estimated payload of 23 pounds Plane weight of 12 pounds