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A supersonic aircraft is designed to operate at 2.0M if thrust loss is required to be less than 2% then determine the reference value of inlet pressure recovery. Given ram recovery Correction factor C is 1.2.(a) 95%(b) 99(c) 102(d) 70I had been asked this question in my homework.Question is from Propulsion topic in chapter Propulsion of Aircraft Design |
Answer» The correct answer is (a) 95% |
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