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MECHANICS OF MATERIALS PROBLEMS CURTISS-WRIGHT ENGINEERING
Course B-4 Seely: Arts. 29-41 CADETTES 16D0-A-124

16D0-1. Fig. 16D0-l shows the cross section of a spruce box wing spar.
The spar is 16 ft. long and cantilevered to the fuselage. Determine
the maximum uniformly distributed load that can be applied
to the wing spar if the unit shearing stress is not to exceed
300 p.s.i. and the unit tensile stress is not to exceed 6,000 p.s.i.

16D0-2. The beam shown in Fig. 16D0-2(a) is partially restrained at the
right end and has a cross section as shown in Fig. 16D0-2(b).
Determine the maximum tensile unit stress in the beam. Ans. 3410 p.s.i.

[image]
FIG. 16D0-1

[image]
FIG. 16D0-2(a)

[image]
FIG. 16D0-2(b)

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