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Consider a supersonic wind tunnel with test section Mach number of 2 and fixed geometry diffuser designed to operate with minimum stagnation pressure...

Consider a supersonic wind tunnel with test section Mach number of 2 and fixed geometry diffuser designed to operate with minimum stagnation pressure losses (smallest diffuser area).
Find the stagnation pressure loss:
a. when the shock stands downstream of the diffuser where the duct area is 5%
larger than at the diffuser throat.
b. when the diffuser is replaced by a piece of straight pipe
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