Modeling of Internal Flow Structures in the Isolator of Scramjet Engines

Abstract

A new modeling concept to predict internal flow structures in scramjet isolator has been introduced. The analytical model proposed in this study consists of mean and fluctuation parts to predict local flow properties in the isolator. The isolator model has been favorably compared with CFD results and experimental data. The CFD considered a typical hypersonic intake and isolator with constant flow channel area and took account of boundary layer effect. The model was applied to various isolator geometry with several inlet flow conditions. NomenclatureA = Area dt = time step H = height i = time index during navigation j = waypoint index M = Mach number p = static Pressure q = gas dynamic function t = time X = distance after the first induced shock wave in isolator  = compression angle  = Specific heat ratio cowl  = cowl angle ij  = viscous stress tensor  = angle of shock wave, period of shock wave reflection

Backpressure propagation mode and balance property in a rectangular duct

“…Similarly, Kamali et al 12 investigated the parametric effect of wall temperature on the shock-train structure using large-eddy simulation and reported that decreasing the wall temperature can control the shock-train behaviour. Moon et al 13 developed a quasi-one-dimensional technique to model a internal flow in scramjet isolator and made comparison with the experimental data and numerical simulation. The result indicated that the analytical method predicts the flow characteristics and structure well.…”