Calculations of the flow fields at the inlet's entrance of the supersonic aircraft using the march second order approximation scheme

Three numerical methods (Lax–Wendroff, Godunov, Godunov–Kolgan–Rodionov) are compared on the example of the transition equation. The Godunov–Kolgan–Rodionov method is chosen for the numerical simulation of the flow fields at the inlet's entrance of the supersonic civil aircraft. Optimal calculation grid, providing optimal correlation between calculation time and accuracy is chosen using the Richardson's extrapolation method. Parametrical calculations for the Ту-144 aircraft at the cruising regimes are performed.