Analysis of flow in the front-mixing region of hypersonic combined-cycle engine

An axisymmetric Navier-Stokes code was developed to analyze the mixing flow in the duct forturbo-ramjet engine. A three-step Runge-Kutta scheme is used to drive the solution toward a steady state. The Lam-Bremhorst Low-Reynolds number k-e model was used to simulate the effect of turbulence on mixing phenomenon. The experiment using a scaled model duct was conducted to validate the numerical code. Comparison with experimental data indicated that computed results successfully captured the important features of mixing flow phenomenon.