A prediction procedure for computing the shock and expansion waves associated with transonic and supersonic flow is presented. In order to assess the capability of the model, calculations are carried out for a number of benchmark cases, for which analytical solutions or published data are available. The cases considered are: supersonic flow over jet vanes; transonic shocked flow in a nozzle; over- and under-expanded free jets with Mach disc formation; and supersonic flow in a cascade of wedges with shock reflection and Prandtl-Meyer expansion. The model, which includes the solution of the steady-state Euler equations as well as the full Navier-Stokes equations, utilizes some modifications made to an existing finite-volume formulation in order to ensure momentum and energy conservation through the shock waves.

In all the cases, the calculations compare favourably with the analytical and experimental results.