Problem $2-[3$ points$]$

Consider an oblique shock generated at a compression corner with a deflection angle $=18\mathrm{.}2.$

A straight horizontal wall is present above the corner. If the upstream flow has the properties

$M_1=4\mathrm{.}0,p_1=1$atm, and $T_1=520R$ :

a$.$ Calculate $M_3,p_3,$ and $T_3$ behind the reflected shock from the upper wall. Aloo, obtain the angle

$$ at which the reflected shock makes with the upper wall. Show all calculations using textbook

table$/$diagrams$.$

b$.$ If the deflection angle $$ is changed, determine at what value of $$ you would first see a Mach

reflection from the upper wall. Is this value of $$ greater than or less than the value in part $1?$

Plot how the reflection angle $$ changes with the change in $.$ May use online compressible flow

calculator.