This project was completed for AERO 405: Supersonic and Hypersonic Aerodynamics. It was a pretty short and concise project that compares the lift, drag, and pitching moment about the leading edge for the GU2 airfoil at Mach=2.13 for a range of angles of attack. The results were compared with respect to linearized theory, Busemann’s method, shock-expansion theory, and wind tunnel results. It was an enjoyable project with code provided below. Note: If you’re checking this out on mobile, the embedded pdf gets a little sluggish. I suggest just clicking the Download Report PDF button.