FINAL PROJECT FEA OF A WING OF FIGHTER PLANE

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Presentation transcript:

FINAL PROJECT FEA OF A WING OF FIGHTER PLANE FACULTY:- PROF JOSE .GRANDA ME 272 (FALL 2006) SUBMITTED BY:- RUPAL PRAJAPATI Student ID:-989-61-7270

FEA OF FALCON FIGHTER PLANE MODEL MADE IN SOLID WORKS AND INSERTED IN NASTRAN 4D

OBJECTIVE Stress Analysis of the wing by applying lift force at the bottom of the wing Vibration Analysis of the wing by applying lift force at the bottom of the wing

VIEWS OF FIGHTER PLANE

MESHING OF THE WING The wing is restraint at one end Wing mesh size is 0.0024 m Wing consist of 15204 Nodes Select the material for the wing body

Forces acting on a plane DRAG FORCE LIFT FORCE THRUST FORCE WEIGHT

Lift Force The weight force of the plane is overcome by the lift force. The magnitude of lift depends on shape, size and velocity of aircraft. L equals Cl times r times v squared over two times A. Lift equals coefficient times density times velocity squared over two times wing area. Coefficient C l contains all the complex dependencies and is usually determined experimentally.

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

FEA OF A WING at 2.63e+5 N FEA of the Wing 2.63e+5 N Max Von Misses stress is 8.62e +10Pa Deformation of the wing is 0.0085

FEA at Lift force of 6.63e+5 N Max Von Misses stress is 2.11e +11Pa Vibration analysis Deformation scaled by 0.106. Frequency 2.17Hz

Conclusion The Von Misses stress exceeds the ultimate tensile stress of the material 2.11e +11Pa > 6e +8Pa Hence the wing fails. The Deformation is scaled by 0.016 Frequency of the body is 2.17Hz

REFERENCE www.google.com www.Howstuffworks .com

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