1. The figure below shows an aircraft wing that is cantilevered from the fuselage (not shown)...

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1. The figure below shows an aircraft wing that is cantilevered from the fuselage (not shown) at location A. The wing has self-weight that can be approximated by the distributed load w(x) = wo(1-x/L) with wo= 100 lb/ft, a = 10 ft, and I = 40 ft. The wing has a small tip tank with weight, Wt= 250 lb, at location C. The wing supports an engine pod with weight, We = 800 lb, hanging under the wing at B. During a stationary run-up on the ground, the engine also produces a torque, Te= 3000 ft-lb. B Fi 'y engine a wing w(x) Hq Litom Te We tip tank Wt (a) Write analytic expressions (symbolically, no numbers) for the shear force, V (x), and the bending moment, M(x), distributions in the wing in terms of the given parameters. (b) Draw the shear force and bending moment diagrams, V (x) and M(x). Label all interesting points with numeric values. 1. The figure below shows an aircraft wing that is cantilevered from the fuselage (not shown) at location A. The wing has self-weight that can be approximated by the distributed load w(x) = wo(1-x/L) with wo= 100 lb/ft, a = 10 ft, and I = 40 ft. The wing has a small tip tank with weight, Wt= 250 lb, at location C. The wing supports an engine pod with weight, We = 800 lb, hanging under the wing at B. During a stationary run-up on the ground, the engine also produces a torque, Te= 3000 ft-lb. B Fi 'y engine a wing w(x) Hq Litom Te We tip tank Wt (a) Write analytic expressions (symbolically, no numbers) for the shear force, V (x), and the bending moment, M(x), distributions in the wing in terms of the given parameters. (b) Draw the shear force and bending moment diagrams, V (x) and M(x). Label all interesting points with numeric values.