A subsonic diffuser flow is steady and adiabatic with inlet Mach number M1 = 0.6. Total pressure loss in the diffuser is 2% of the inlet total pressure, i. e., pt2/ pt1 = 0.98. The diffuser area ratio is A2/ A1 = 1.50. Assuming that the flow in the diffuser has a uniform exit flow, calculate the exit Mach number M2 the static pressure recovery in the diffuser CPR the (internal) force acting on the diffuser, i. e., Fx, wall, nondimensionalized by the inlet static pressure and ar