(Solved): A planar two-dimensional wedge and resulting oblique shock is used with a normal shock in an inlet ...

A planar two-dimensional wedge and resulting oblique shock is used with a normal shock in an inlet for an aircraft that flies at a Mach number of \( M_{a}=2.25,(\gamma=1.4) \) at an altitude with a static pressure of \( p_{a}=8 \mathrm{psia} \). A half-wedge angle of \( \delta=20^{\circ} \) is used. The internal pressure recovery is \( \pi_{r}=0.95 \). (a) What is the Mach number behind the oplique shock? \( 1.42 \) \( 2.13 \) \( 1.08 \) \( 1.85 \) (b) What is the total pressure ratio \( \pi_{d} \) at the exit of the diffuser? \( 1.03 \) I. 19 (b) What is the total pressure ratio \( \pi_{d} \) at the exit of the diffuser? \( 1.03 \) I.19 \( 0.79 \) \( 0.6 \) (c) What is the total pressure \( [ \) psia \( ] \) at the exit of the diffuser? \( 58.5 \) 102 \( 43.9 \) \( 73.1 \)