$($Show work and steps for all parts. Circle$/$box final answers$)$

Problem $2$

Air flowing at Mach $2$ with a pressure of $80$ kPa and a temperature of $30^($@$)$C passes over a component

of an aircraft that can be modeled as a wedge with an included angle of $8^($@$)$ that is aligned with the

flow, i$.$e$.,$ the flow is turned by both the upper and lower surfaces of the wedge through an angle of

$4^($@$),$ leading to the generation of an oblique shock wave. Determine the following:

a$)$ The loss in the total pressure.

b$)$ Mach number of the flow downstream of the shock.

c$)$ Static and Stagnation Temperature downstream the shock wave

d$)$ The pressure acting on the surfaces of the wedge.

e$)$ The velocity downstream the chock.