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 halfspan 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 7075T6. 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
 Kim
 Force, Airfoil, 30 degree, transverse shear force

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