Abstract In this study, the effects of the shock wave on sonic transverse hydrogen through single and multi-jets for supersonic combustion were investigated numerically. This study presents the fundamental flow physics of the interaction between fuel jets (single or multi array) and incident shock waves into a Mach 4.0 crossflow. Parametric studies were conducted on the performance of the shock wave by using the RANS equations with Menter's Shear Stress Transport turbulence model. In a parametric study, both the streamwise spacing and jet-to-freestream total pressure ratio are varied. For all downstream mixing, the associated flow behavior was found to be a direct result of both the type of injection (single/Multi jet) and interactions between shock waves and injectors. According to the results, shock wave reduces the maximum concentration of the hydrogen jet more than 20% in both single and multi jet. Furthermore, a significant increase (approximately 40%) occurs in the mixing of the hydrogen jet at downstream when shock generator is presented in the multi jet with PR=0.27. Moreover, hydrogen-air mixing rate extends in streamwise direction as the jet space increases. Thus, an enhanced mixing zone occurs in the in far downstream of the jet and the shock wave.