Fundamentals of Aerodynamics 2024, 47: Linearized Supersonic Flow

As always, first we need an expression for the pressure coefficient. It emerges from a differential equation with boundary condition in relation to the Mach number and Mach angle μ. This creates a series of solutions parallel to the Mach line, sloping downstream above the airfoil. This also means that disturbances can only propagate upstream in a steady supersonic flow. Since we're focusing on linearized flow, said perturbations will remain small, and by the usual process, arrive at the pressure coefficient