Assuming the inlet captures the entire flow at all flight Mach numbers, and the internal pressure is always high enough to stabilize a normal shock at the entrance of the internal duct, calculate and plot the stagnation pressure ratio across the combined shock system for the above flight Mach numbers.

The air in an automobile tire with a volume of 0.015 m3 is at 32°c and 140 kpa gage. determine the amount of air that must be added to raise the pressure to the recommended value of 206 kpa gage. assume the atmospheric pressure to be 128 kpa and the temperature and the volume to remain constant.[r-0.287 kj/kgk]