Engineering, 27.10.2020 17:40 victor49
Assuming the inlet captures the entire flow at all flight Mach numbers, and the internal pressure is always high enough to stabilize a normal shock at the entrance of the internal duct, calculate and plot the stagnation pressure ratio across the combined shock system for the above flight Mach numbers.
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Assuming the inlet captures the entire flow at all flight Mach numbers, and the internal pressure is...
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