Supersonic flow over a Cone

Numerical Solutions to the Taylor-Maccoll Equation are obtained using 4th order Runge-Kutta Method for a supersonic flow over a cone.

The files provides the numerical procedures used to solve oblique shock relation and Taylor-Maccoll equation. 4th-order Runge-Kutta numerical scheme is employed to implicitly solve the Taylor-Maccoll equations.

Inverse approach is used (J.D. Anderson, Modern Compressible Flow, Section 10.4)

Properties of the flow are calculated for

- A supersonic Mach number

- Zero pitch and yaw

- An in-viscid, perfect gas

Note - The generated shock wave is 3D in nature but as the shock is locally planar, thus is treated locally by the use of 2D oblique shock theory.