Critical evaluation of three-dimensional supersonic combustor calculations
Abstract
A nonreacting supersonic combustor case is studied with a Navier-Stokes CFD code using a k - epsilon two-equation turbulence model. The numerical scheme is based on a pressure correction algorithm solving the Full Navier-Stokes equations. The present combustor test section is configured with staged, transverse injectors located behind a rearward-facing step. The effect of the turbulent Schmidt number on mixing, penetration, and spreading rates associated with transverse injection is extensively investigated by comparing calculations with experimental data.
- Publication:
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AIAA, Aerospace Sciences Meeting
- Pub Date:
- January 1990
- Bibcode:
- 1990aiaa.meetQU...R
- Keywords:
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- K-Epsilon Turbulence Model;
- Navier-Stokes Equation;
- Supersonic Combustion;
- Three Dimensional Flow;
- Backward Facing Steps;
- Computational Fluid Dynamics;
- Predictor-Corrector Methods;
- Schmidt Number;
- Fluid Mechanics and Heat Transfer