LAUSR

Abstract The rate of fuel mixing inside the combustor is highly significant and effective on the performance of the scramjet engine. In this study, numerical simulations are applied to study the influence of the sinusoidal shock generator on the flow structure of the multi hydrogen jet at supersonic crossflow. The primary focus of this research is to perform flow analysis to determine the role of the shock interaction produced by the presence of the shock generator on the rate of mixing in the downstream of the fuel jets. To simulate the flow, the CFD method with the K-w turbulence model is applied to capture the shock formation inside the domain. According to our results, the mixing rate increases by approximately 40% as the amplitude of the sinusoidal shock generator increases from 2 to 5 mm. Besides, it is found that the fuel distribution becomes uniform when the produced shock generator is more strengthen.