Numerical study of shockwave/boundary layer interactions in premixed hydrogenair hypersonic flows
Abstract
A computational study of shock wave/boundary layer interactions involving premixed combustible gases, and the resulting combustion processes is presented. The analysis is carried out using a new fully implicit, total variation diminishing (TVD) code developed for solving the fully coupled Reynoldsaveraged NavierStokes equations and species continuity equations in an efficient manner. To accelerate the convergence of the basic iterative procedure, this code is combined with vector extrapolation methods. The chemical nonequilibrium processes are simulated by means of a finiterate chemistry model for hydrogenair combustion. Several validation test cases are presented and the results compared with experimental data or with other computational results. The code is then applied to study shock wave/boundary layer interactions in a ram accelerator configuration. Results indicate a new combustion mechanism in which a shock wave induces combustion in the boundary layer, which then propagates outwards and downstream. At higher Mach numbers, spontaneous ignition in part of the boundary layer is observed, which eventually extends along the entire boundary layer at still higher values of the Mach number.
 Publication:

AIAA, Aerospace Sciences Meeting
 Pub Date:
 November 1990
 Bibcode:
 1990aiaa.meet....7Y
 Keywords:

 Air;
 Boundary Layers;
 Combustion Physics;
 Gas Mixtures;
 Hydrogen;
 Hypersonic Flow;
 Premixing;
 Shock Layers;
 Shock Wave Interaction;
 Shock Waves;
 Tvd Schemes;
 Average;
 Chemical Reactions;
 Combustion;
 Continuity Equation;
 Convergence;
 Extrapolation;
 Flammable Gases;
 Ignition;
 Iteration;
 Mach Number;
 NavierStokes Equation;
 Reynolds Equation;
 Fluid Mechanics and Heat Transfer