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 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. Correct Answer 95%
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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Feb 20, 2025