$3.[10$ points$]$ Consider the symmetric, diamond$-$shaped section $($as shown below$)$ exposed

to a Mach number of $2\mathrm{.}20$ with a stagnation pressure P t $=125$ psia, and Tt $=600$o R$.$ The

airfoil has a maximum thickness of $7\%,$ and an angle of attack of $6$o $.$

a$.$ Using shock$/$expansion theory, calculate the pressures at regions $2$ through $5$

b$.$ Using linear supersonic theory, calculate the pressures at regions $2$ through $5$

c$.$ Calculate lift and drag coefficients for both cases. Comment on the differences.