This project attempts to compute the “optimal” ramp for a 2-D supersonic jet inlet. The “optimal” ramp here is defined as a ramp that allows the incoming airflow to experience as little loss of stagnation pressure. The constraint is that the shock waves that is used to slow the airfoil must all be contained within the engine inlet so it does not cause massive wave drag to other components, this calls for a series of gradual oblique shock waves impinging on a single point at the engine inlet. More details will be provided in the documentation.

This proejct has the bulk of its computation performed in C++, but post-processing of producing the various plots is handled using Python and the matplotlib library.

The code documentation is poor and very lacking.