$(30$ pts$)$ Write a numerical algorithm $($computer code$)$ that solves for the change in flow

properties across a series of oblique shock waves followed by a normal shock wave. In

other words, create a numerical algorithm that solves for the change in flow properties

across a supersonic inlet.

a$.(5$pts$)$ Verify your algorithm is correct by comparing the code output with the

hand calculations done in class for the Mach $3$ inlet with $3$ shocks where both

wedge angles are $15$ degrees.

b$.(15$pts$)$ Use your algorithm to recreate the results shown in the plots provided in

the notes. Specifically, solve for the wedge angle$($s$)$ that maximize total pressure

recovery for different Mach numbers. Then:

i$.$ Plot optimum wedge angle for a $2$ shock inlet as a function of Mach

number

ii$.$ Plot optimum wedge angles for a $3$ shock inlet as a function of Mach

number

Double wedoe inler $(3$ shocks$)$

iii. Make a plot showing optimum $($maximum$)$ total pressure recovery for $1$

shock, $2$ shock, $3$ shock systems as a function of Mach number.

c$.(10$pts$)$ Use your algorithm to plot the total pressure recovery as a function of

Mach number for a $3$ shock inlet where both wedge angles are $15$ degrees. c$.(10$pts$)$ Use your algorithm to plot the total pressure recovery as a function of Mach number for a $3$ shock inlet where both wedge angles are $15$ degrees.