final project fea of a wing of fighter plane faculty:- prof jose.granda faculty:- prof jose.granda...
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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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