MECHANICS OF MATERAILS PROBLEMS CURTISS-WRIGHT ENGINEERING
Course B-4 Seely: Arts. 33-41; 116-131; CADETTES 21D0-A-129
21D0-l. Fig. 21DO-l shows a 4-motored low-wing monoplane in flight. Each wing
has four aluminum alloy spars with the cross-section at the root as
shown in Fig. 21D0-2. Assume the loads to be evenly distributed among
the 4 spars.
For the loading shown,
(a) Draw complete shear and noment[moment] diagrams.
(b) Determine the maximum fiber unit stress and state where it occurs.
Assume constant cross-section for a spars, and neglect the effect
of the rivet holes.
(c) Determine the shearing unit stress at a point 2 in. from the top
on a section where the total shear is maximum.
(d) Determine the deflection the wing tip would have if the spars
were of constant cross-section, and there were no rotation at the
root (that is, assume the spars fixed at the fuselage) for,
(a) The motor loads alone.
(b) The distributed load alone.
Fuselage Reaction Points
Notes and Questions
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