FINAL PROJECTFINAL PROJECTFEA OF A FEA OF A WINGWING OF OF FIGHTERFIGHTER PLANE PLANE

FACULTY:- PROF JOSE .GRANDAFACULTY:- PROF JOSE .GRANDA ME 272 (ME 272 (FALL 2006FALL 2006))

SUBMITTED BY:- RUPAL SUBMITTED BY:- RUPAL PRAJAPATIPRAJAPATI

Student ID:-Student ID:-989-61-7270989-61-7270

FEA OF FEA OF FALCONFALCON FIGHTER PLANE FIGHTER PLANE

F 16 FALCON F 16 FALCON FIGHTER PLANEFIGHTER PLANE

MODEL MADE IN SOLID MODEL MADE IN SOLID WORKS AND INSERTED WORKS AND INSERTED IN NASTRAN 4DIN NASTRAN 4D

OBJECTIVEOBJECTIVE Stress Analysis of the wing by applying lift force at Stress Analysis of the wing by applying lift force at

the bottom of the wingthe bottom of the wing Vibration Analysis of the wing by applying lift force Vibration Analysis of the wing by applying lift force

at the bottom of the wingat the bottom of the wing

VIEWS OF FIGHTER PLANEVIEWS OF FIGHTER PLANE

MESHING OF THE WINGMESHING OF THE WING

The wing is restraint at one endThe wing is restraint at one end Wing mesh size is 0.0024 mWing mesh size is 0.0024 m Wing consist of 15204 NodesWing consist of 15204 Nodes Select the material for the wing bodySelect the material for the wing body

Forces acting on a planeForces acting on a plane

DRAG FORCEDRAG FORCE LIFT FORCELIFT FORCE THRUST FORCETHRUST FORCE WEIGHTWEIGHT

Lift ForceLift Force The weight force of the plane is overcome by the lift force.The weight force of the plane is overcome by the lift force. The magnitude of lift depends on shape, size and velocity The magnitude of lift depends on shape, size and velocity

of aircraft.of aircraft.

L equals Cl times r times v squared over two times A.L equals Cl times r times v squared over two times A. Lift equals coefficient times density times velocity squared Lift equals coefficient times density times velocity squared

over two times wing area.over two times wing area. Coefficient C l contains all the complex dependencies and Coefficient C l contains all the complex dependencies and

is usually determined experimentally. is usually determined experimentally.

Calculation of Lift ForceCalculation of Lift Force

CL (Lift coefficient) =0.55CL (Lift coefficient) =0.55 Density of air = 0.00237slug/ft3Density of air = 0.00237slug/ft3 Velocity =2200ft/secVelocity =2200ft/sec Area of wing =322 square feetArea of wing =322 square feet Weight of total body=16875 KgWeight of total body=16875 Kg Thrust =130KNThrust =130KN Speed =1500mphSpeed =1500mph Mach No =2Mach No =2 Max Altitude is 50,000 ftMax Altitude is 50,000 ft Air Pressure at 50,000ft is 11.65KPaAir Pressure at 50,000ft is 11.65KPa Weight of wing =6000KgWeight of wing =6000Kg LIFT FORCE =149100 lbsLIFT FORCE =149100 lbs

FEA OF A WING at 2.63e+5 NFEA OF A WING at 2.63e+5 N

FEA of the Wing 2.63e+5 NFEA of the Wing 2.63e+5 N Max Von Misses stress is 8.62e +10PaMax Von Misses stress is 8.62e +10Pa Deformation of the wing is 0.0085Deformation of the wing is 0.0085

FEA at Lift force of 6.63e+5 NFEA at Lift force of 6.63e+5 N Max Von Misses stress is Max Von Misses stress is

2.11e +11Pa2.11e +11Pa Vibration analysisVibration analysis Deformation scaled by 0.106.Deformation scaled by 0.106. Frequency 2.17HzFrequency 2.17Hz

ConclusionConclusion

The Von Misses stress exceeds the ultimate The Von Misses stress exceeds the ultimate tensile stress of the materialtensile stress of the material

2.11e +11Pa > 6e +8Pa2.11e +11Pa > 6e +8Pa Hence the wing fails.Hence the wing fails. The Deformation is scaled by 0.016The Deformation is scaled by 0.016 Frequency of the body is 2.17HzFrequency of the body is 2.17Hz

REFERENCEREFERENCE

www.google.comwww.google.com www.Howstuffworkswww.Howstuffworks .com .com

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