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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%

To EXPLAIN I would say: Reference PRESSURE recovery = (THRUST loss/C) + ACTUAL pressure recovery

= 0.02/1.2 + 0.93

= 0.016+0.93 = 0.95 = 0.95*100% = 95%.



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