A numerical study of the effects of geometry on the performance of a supersonic combustor

A numerical study is conducted to investigate the effects of two combustor scale parameters, the expansion angle and the length of the constant area combustor section, on the mixing and combustion within a supersonic combustor. This study uses the SPARK 3D Navier-Stokes code. Turbulence is modeled utilizing an algebraic eddy viscosity model and the chemical mechanism is modeled with a 7-reaction, 7-species finite-rate chemistry model. The calculations show that, even at the relatively low flight Mach numbers (5-7) associated with the conditions examined, the chemical constituents are far from equilibrium, and therefore that kinetics effects are important.