Numerical Study of Unsteady Shock-Induced Combustion in Scramjet Engine

초록

A numerical analysis has been conducted to study the interaction between combustion dynamics and supersonic flows in a combustion chamber of a scramjet engine. The complete conservation equations of mass, momentum, energy, and species are formulated for the two-dimensional combustion chamber. Variable thermo-physical properties and finite-rate chemical reactions are accommodated to study the detailed flame dynamics. In order to check the feasibility of the numerical scheme, the steady state calculation results have been compared to the experimental results of a dump-type supersonic wind-tunnel. The steady state calculation results have been also fully visualized.