Question

An aircraft wing is subject to a lift distribution that is equivalent to the distributed load w(x) = wo (1-x2) Treat the wing as a cantilevered beam with flexural rigidity EI and a rectangular cross-section with width b and height h. The cross section is constant along the length of the wing. The maximum compressive and tensile stresses are each Go. W(X) El Calculate: The deflected shape v(x) The tip deflection v(L) If the width of the wing cross-section b is known, find the height of the wing cross- section, h, that ensures the factor of safety is 1.5 everywhere in the wing b. c.

Answer 1