关键词: 射流;超音速流;分离;流场;数值解

Abstract: Issuing a jet stream into a supersonic external flow is a common technique for flight control of aerospace vehicles. In this paper, MacCormack explicit scheme and Baldwin-Lomax algebraic turbulent model are employed to solve the 2D compressible RANS equations for the numerical simulation of the supersonic and hypersonic external flow over a rearward facing step with transverse injection. The velocity vector field, pressure contour of the field are given for understanding of the interaction phenomina and comparison. The interaction effects increase with the width of slot, but are insensitive to the Mach number of free stream. Adding the fourth-difference dissipation to a central difference scheme in no shock regions can promote the convergence rate and is necessary for the hypersonic problem with transverse injection. The obtained results may be used for the preliminary design of maneuver missiles.

Key words: Jet flow;Supersonic flow;Separation;Flow field;Numerical solution