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

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

3. 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

4. VIEWS OF FIGHTER PLANE

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

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

7. 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.

8. Calculation of Lift Force
CL (Lift coefficient) =0.55
Density of air = slug/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 = lbs

9. 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

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

11. 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

12. REFERENCE
.com

13. Thanks