Ram Compression on Turbojet/Turbofan Thrust
Does anybody have a formula for determining the effects of ram-compression on thrust levels for turbojet/turbofan engines at subsonic and supersonic speed?
Also, when it comes to air compression -- is there a point where air will reach a pressure at which it won't proportionately compress right (i.e. you have a 9:1 pressure ratio, the inlet has increased the atmospheric pressure to 10 atmospheres, so when the air flows through the compressor after coming off the inlet, it is about 90 atmospheres. Is there a point where if you were flying at high supersonic speeds where the compression off the inlet would be so high that when you run the air though the compressor, it wouldn't increase the pressure 9-fold?)?