Unformatted text preview: quarter of the chord from leading edge (c/4 line) at angle of 30 degree. 1. Formulate an expression for lift w as a function of the span location x . The total lift is the weight of the plane times the load factor 2.5. Plot the lift w over the half-span of the wing: x = [0, L /2]. Explain your formulation. 2. Derive the relationship for the transverse shear force V , bending moment M as a function of span location x . Calculate the transverse shear force V , bending moment M and torque T at the wing root section. Calculate the maximum von Mises stress at the root and compare it with yield strength of the material. Assume the wing is made of Aluminum 7075-T6. Weight of the plane 350,000lb Wing span L 1,858in Root width c root 251.6in Root height h root 49in Thickness of plate t 1.0in Load factor 2.5 Sweep angle c/4 chord line x y L /2 b c tip c root h root...
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- Spring '09
- Force, Airfoil, 30 degree, transverse shear force