Abstract

A computational fluid dynamic code based upon the Reduced Navier Stokes (RNS) equations has been studied for its applicability to supersonic combustion ramjet (scramjet) inlet isolators. The RNS procedure is an attractive way to accelerate convergence for a wide range of flow problems. A global relaxation algorithm based on the RNS equations is utilized in a space-marching mode. The space-marching procedure is similar to that used for solution of the Parabolized Navier Stokes (PNS) equations, but multiple sweeps from inflow to outflow allow for streamwise ellipticity not accounted for in PNS solutions. The RNS results are compared to the time-marching, full Navier Stokes procedure contained in the General Aerodynamic Simulation Program (GASP) CFD code.

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