Andrew Fleming Gregory Palm Rebekah Puterbaugh Team Advisor: Dr. Scott Thomas

College of Engineering and Computer Science

Department ofMechanical and Materials Engineering

Wright State UniversityRegular Class Aircraft

SAE Aero Design East Competition

“Raiders”

Team Number 020

Andrew FlemingGregory Palm

Rebekah Puterbaugh

Team Advisor: Dr. Scott ThomasTeam Pilot: Eddie Noble

April 16, 2004



Design with high-lift criteria in mind Meet all design competition requirements Built so pilot can easily control the plane Minimize weight wherever possible Have working plane with multiple test flights

prior to the competition

Project Goals



Airfoil Selection High-lift airfoil required Three designs singled out

– Selig 1223– Selig 1210– NACA 6412

XFOIL used to determine airfoil performance– Angle of attack = 0 degrees– Re = 310000– Mach = .0221– Flap deflection = 0 degrees

Selected Airfoil– Selig 1223

cl cm cd

S1223 2.0249 -0.259 0.02464

S1210 1.8810 -0.230 0.01884

NACA 6412 1.5036 -0.139 0.01557



Engine Test Stand Designed by Wright State Aero

Design Team 2003 Initially for engine “break-in” Primarily for static thrust

measurements using various propellers

Propeller RPM Thrust Produced (lbs.)

10 x 8 Zinger 14500 4.75

11 x 7 Masterscrew 13290 6.00

13 x 5 Zinger 10740 7.90

13 x 6 APC 10690 8.70

14 x 6 Zinger 8280 7.75

15 x 6 APC 7000 6.50



Simultaneous equations with time as driving variable

Chord length and density referenced for instant updates

From initial time to liftoff From goal weight and required

takeoff distance, determined chord length

CalculationsLift

Wing Drag

Fuselage Drag

Δtavv 1i1ii

Δtvdd 1i1ii

SρVC2

1D 2

wingD,Wing

frontal2

Area Fuselage AρV2

1D

ctionRollingFriEffectiveRolling μWD

RollingeaFuselageArWingTotal DDDD

LWWW PayloadAirplaneEffective

iTotal,ixNet, DTmaT SVρC

2

1L 2

L Rolling Drag

Effective Weight

Total Drag

Net Thrust/Acceleration

Total Distance

Instantaneous Velocity



Construction Methods Fuselage

– Foam laminated with balsa on one side

Nose– Balsa build-up

Wings– Balsa build-up

Tail– Foam laminated with balsa sheeting on

both sides



Plane taxied in the parking lot of Russ Engineering Center

Lift-off with a small payload Design Improvements

– Lightening process Lightening holes located in tail and rear

fuselage Lighter rear landing gear Net weight loss: .91 lbs.

– New nose gear

– Cross members located closer to wing

Taxi Test: March 27, 2004



Several parameters adjusted– Propeller– Payload– Flap Deflection

Top Result– 13 x 6 APC Propeller– 40% Flap deflection– Approximately 180 feet for takeoff

Design Improvements– Taller gear set– Adjustment of payload base– Small rear drag wheel– Fixed elevator servo

Takeoff Test 1: April 7, 2004



Failures– Nose gear

– Rear landing gear

Design Improvements– Improved soldering on nose gear

extension

– Reinforced rear landing gear mount

Takeoff Test 2: April 10, 2004



Estimated total plane costs: $1,354.12

Major Cost Breakdown

Budget



Project Timeline

11/15/2003 12/5/2003 12/25/2003 1/14/2004 2/3/2004 2/23/2004 3/14/2004 4/3/2004 4/23/2004 5/13/2004

Overall Project

Design

Construction

Fuselage

Tail

Wings

Electronics

Landing Gear

General Assembly

Testing/Modifications

Competition

Weekly Update Meetings

Paper



R/C Aircraft Building Skills– Phases of the project take longer than anticipated

– Optimizing aircraft for top performance

– Basic R/C model building skills

– Engine testing and fine tuning

Team Building Skills– Project phase planning

– Optimizing work time for each team member

– Solving design conflicts

Lessons Learned



Flight Test Video



Questions?



Design Page #1



Design Page #2



Design Page #3



Design Page #4



Design Page #5

Andrew Fleming Gregory Palm Rebekah Puterbaugh Team Advisor: Dr. Scott Thomas

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