Discussion
A cylindrical fuselage of radius \( 2 \) m and skin thickness \( 1.6 \) mm carries a cabin differential of \( 55 \) kPa. The hoop stress is nearest to
Answer: B
The thin-shell hoop stress is \( pr/t = 55\,000 \times 2 / 0.0016 = 68.8 \times 10^6 \) Pa, that is 68.8 MPa. Against an aluminium yield near 300 MPa this leaves ample static margin, but it is the cyclic repetition of it that governs the design.
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