At the exit of the diffuser of a supersonic wind tunnel which exhausts directly to the atmosphere,

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At the exit of the diffuser of a supersonic wind tunnel which exhausts directly to the atmosphere, the Mach number is very low \((\approx 0.1)\). The reservoir pressure is \(1.8 \mathrm{~atm}\), and the test section Mach number is 2.6. Calculate the diffuser efficiency \(\eta_{D}\).

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