$($a$)(2$ points$)$ What type of inlet is this? Ans: Blank $1.$

$($b$)(2$ points$)$ Identify the region$($s$)$ where the flow is supersonic. Ans: Blank $2$

Use the 'Compressible Aerodynamics Calculator' to complete the following parts. Round all your answers to two decimal places.

$($c$)(2$ point$)$ Find the shock wave angle for the first shock. Ans: Blank $\backslash (3^\{\backslash$circ$\}\backslash ).$

$($d$)(2$ point$)$ Find $\backslash (\backslash$mathrm$\{$M$\}\_\{2\}\backslash ).$ Ans: Blank $4.$

$($e$)(3$ points$)$ Find $\backslash ($ M$\_\{3\}\backslash ).$ Ans: Blank $5.$

$($f$)(2$ points$)$ Find the deflection angle of the third shock. Ans: Blank $\backslash (6^\{\backslash$circ$\}\backslash ).$

$($g$)(3$ points$)$ Find $\backslash (\backslash$mathrm$\{$M$\}\_\{4\}\backslash ).$ Ans: Blank $7.$

$($h$)(3$ points$)$ Find $\backslash (\backslash$mathrm$\{$M$\}\_\{5\}\backslash ).$ Ans: Blank $8.$