Three-dimensional Computational Analysis of Transverse Injection in a Supersonic Combustor

Abstract

The scramjet engine plays a promising role for a successful future hypersonic flight system. The performance of scramjet system depends on many factors like mixing rate of fuel and air, proper flame stabilization mechanism and suitable injection system. The flame stabilization is provided by means of introducing a Cavity along the wall of the combustor. The cavity effects on the performance of supersonic combustion will be studied here with the help of three-dimensional combustor CFD model. The reliability of the numerical results obtained by using the computational approach depends on the proper validation of the CFD code with their corresponding experimental results. The corresponding experimental results from the literature will be identified and used here for the validation of the numerical code. The final CFD results after its validation with the experimental results will be presented in terms of x-y plots and contours for the discussion.