Numerical predictions of a rearward-facing-step flow in a supersoniccombustor

Abstract

A computational fluid dynamics (CFD) code has been developed to compute the mixing and combustion of hydrogen fuel in the turbulent flowfields of supersonic combustion ramjets (scramjet) with primary interest for the case of transversely injected fuel. The code solves the three-dimensional time-dependent Reynolds-averaged Navier-Stokes equations, including species transport for a four-species, two-reaction, global finite-rate-chemistry model. Numerical integration was obtained by MacCormack's explicit method, and turbulence was modeled by the eddy viscosity model of Baldwin-Lomax. Mass diffusion was based on Pick's Law, and unit Lewis number was assumed. The code has been validated by comparing computational results with existing experimental data and applied to simulate a realistic scramjet combustor flowfield, particularly in the vicinity of the fuel injectors. Results from the comparisons are presented and discussed.