Group 3Heavy 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

FlapFlap AileronAileron

C

.25C

35-40% 60-65%

100%

Technical Analysis: VelocityFlaps fully down at 40 deg.

=24.18 mph=35.47 ft/s

2/1max, )**(

]3519*[wingavg

ozs ACl

WV

sto VV *2.1 =29.02 mph=42.56 ft/s

sl VV *3.1

Takeoff Velocity

Landing Approach Velocity

=31.44 mph=46.11 ft/s

Cruise Velocity

2/1)****2( pLc ACCWV =35.07 mph

=51.43 ft/s

Stall Velocity

Technical Analysis: Landing CL

Takeoff Velocity

increasedesignflappeddesign CLCLCL , =2.5659

designu CLAX *

flappeddesignf CLAY ,*

=915.13

=2195.41

YX

wingavg A

YXCL max,

3110.547

=2.160

Technical Analysis: Lift CalculationAt .7Vto

T = Static Thrust Available = 11.865Fc = Coefficient of Rolling Friction = 0.035

AVCLL to *)7(.***5. 2 =17.105

)(*)[( LWFDTwga cmean =6.684

mean

tog a

VS*2( )2

=135.52 ftWith a 25% safety factor = 169.397

Technical Analysis: Landing CalculationAt .7Vl

W = 35 lb. = 560 oz.Fc = Coefficient of Rolling Friction = 0.035

AVCLL l *)7(.***5. 2 =24.47

)))(*(*2/()*)(( 2 LWFDgWVS ctl =376.67

Plan for Phase III

• Complete Final Design• Create CAD models of Aircraft• Use CAD models to analyze final Aircraft

design

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

ME 423 Phase II Nugget Chart – Design Selection and Technical Analysis