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.
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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.
Cite As
Dyuman Joshi (2026). Supersonic flow over a Cone (https://uk.mathworks.com/matlabcentral/fileexchange/91055-supersonic-flow-over-a-cone), MATLAB Central File Exchange. Retrieved .
General Information
- Version 1.1.0 (23.7 KB)
MATLAB Release Compatibility
- Compatible with any release
Platform Compatibility
- Windows
- macOS
- Linux
