6-38. The dead-weight loading along the centerline of the airplane wing is shown. If the wing is fixed to the fuselage at A, determine the reactions at A, and then draw the shear and moment diagram for the wing.
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Replace each distributed load w(x) by an equivalent resultant force R = w·L acting at the centroid of that distribution (for uniform w, at the midpoint of the loaded length). Label distances from A to each resultant and to each concentrated load. Show more…
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