Question

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) 70

I had been asked this question in my homework.

Question is from Propulsion topic in chapter Propulsion of Aircraft Design

Answer 1

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%.