Discussion
For the same fuselage, the longitudinal stress from pressurisation is
Answer: C
The longitudinal stress is \( pr/2t \), exactly half the hoop value, so \( 68.8/2 = 34.4 \) MPa. That the hoop stress is twice the longitudinal is why pressurisation cracks in a fuselage skin characteristically run along the fuselage rather than around it.
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