Consider a diamond$-$wedge airfoil such as shown in Figure $1,$ with a half$-$angle $\backslash$theta $=10$o$.$ The

airfoil is at an angle of attack $\backslash$alpha $=15$o to a Mach $3$ freestream. Calculate the Mach number

and pressure in region $2$ and $3.$ solve this qn with diagrams