Numerical investigation of supersonic turbulent boundary layers with high wall temperature
Abstract
A direct numerical approach has been developed to simulate supersonic turbulent boundary layers. The mean flow quantities are obtained by solving the parabolized Reynolds-averaged Navier-Stokes equations (globally). Fluctuating quantities are computed locally with a temporal direct numerical simulation approach, in which nonparallel effects of boundary layers are partially modeled. Preliminary numerical results obtained at the free-stream Mach numbers 3, 4.5, and 6 with hot-wall conditions are presented. Approximately 5 million grid points are used in all three cases. The numerical results indicate that compressibility effects on turbulent kinetic energy, in terms of dilatational dissipation and pressure-dilatation correlation, are small. Due to the hot-wall conditions the results show significant low Reynolds number effects and large streamwise streaks. Further simulations with a bigger computational box or a cold-wall condition are desirable.
- Publication:
-
Studying Turbulence Using Numerical Simulation Databases. V: Proceedings of the 1994 Summer Program
- Pub Date:
- December 1994
- Bibcode:
- 1994stun.proc..245G
- Keywords:
-
- Compressibility Effects;
- Computational Fluid Dynamics;
- High Temperature;
- Kinetic Energy;
- Navier-Stokes Equation;
- Reynolds Equation;
- Supersonic Boundary Layers;
- Turbulent Boundary Layer;
- Wall Temperature;
- Computational Grids;
- Free Flow;
- Low Reynolds Number;
- Supersonic Speed;
- Fluid Mechanics and Heat Transfer