The numerical Navier-Stokes solution of two-dimensional flow with transverse injection
Abstract
Injecting a jet stream into a supersonic external flow is a common technique for flight control of aerospace vehicles. In this paper, the MacCormack explicit scheme and the Baldwin-Lomax algebraic turbulence model are employed to solve the two-dimensional compressible Reynolds-averaged Navier-Stokes equations for supersonic and hypersonic external flow over a rearward-facing step with transverse injection. The velocity vector field and the pressure contour of the field are given to clarify the interaction phenomena. The interaction effects increase with the width of the slot, but are insensitive to the freestream Mach number. Adding the fourth-difference dissipation to a central difference scheme in shock-free regions can increase the convergence rate and is necessary for the hypersonic problem with transverse injection.
- Publication:
-
Journal of Propulsion Technology
- Pub Date:
- February 1991
- Bibcode:
- 1991JPT.........24W
- Keywords:
-
- Gas Injection;
- Navier-Stokes Equation;
- Supersonic Jet Flow;
- Two Dimensional Flow;
- Compressible Flow;
- Computational Fluid Dynamics;
- Flight Control;
- Free Flow;
- Fluid Mechanics and Heat Transfer