Consider a subsonic engine inlet (i. e., a diffuser) with an inlet area of 2.30 × 103 in2 and exit-to-inlet area ratio of 1.44. air enters the diffuser flowing at 10.0 lbm/s with a static pressure of 5.00 psia and a velocity of 365 ft/s. the gases exit the diffuser at a static pressure of 5.40 psia and a velocity of 174 mph. assume that the ambient (external) pressure on the walls of the diffuser is 4.90 psia.