A numerical method using AUSMDV scheme and k-ω SST turbulence model with an explicit compressibility correction was developed,and a 3-D numerical simulation of a supersonic flow field with a vertical sonic jet of hydrogen was performed.Good agreement between numerical results and experimental data validated the reliability of the numerical method.Whereafter,two parameters,mass-weighted average total pressure and mixing efficiency,were defined to evaluate the mixing performance of different injection schemes.Based on the numerical method and evaluation criterion,the mixing characteristics of different injection schemes were studied in detail.It was found that for the mixing field of supersonic transverse jet,the near-field mixing is controlled by convection transport while the far-field mixing is controlled by mass diffusion;the circular-hole injection causes a loss of total pressure comparable to the slot injection,but can induce a much higher mixing efficiency because of its 3-D flow characteristic;the variation of injection angle under circular-hole injection mainly affects the near-field mixing degree,and among the five injection angles studied in the present paper,angle 120° is the optimal one;with the increase of the ratio between injector space and diameter,the induced mixing efficiency increases while the caused loss of total pressure can grow greatly;the two-stage injection method designed through reducing the injector area to keep the same hydrogen mass flowrate can induce a much higher mixing efficiency while only a bit larger loss of total pressure when compared to the single-stage injection,and hence the two-stage injection is superior to the single-stage injection.The research results can direct the design of the fuel injection method in the combustor of scramjet engine. A numerical method using AUSMDV scheme and k-ω SST turbulence model with an explicit compressibility correction was developed, and a 3-D numerical simulation of a supersonic flow field with a vertical sonic jet of hydrogen was performed. Good agreement between numerical results and experimental data validated the reliability of the numerical method. Hereafter, two parameters, mass-weighted average total pressure and mixing efficiency, were defined to evaluate the mixing performance of different injection schemes. Based on the numerical method and evaluation criterion, the mixing characteristics of different injection schemes were studied in detail. It was found that for the mixing field of supersonic transverse jet, the near-field mixing is controlled by convection transport while the far-field mixing is controlled by mass diffusion; the circular-hole injection causes a loss of total pressure comparable to the slot injection, but can induce a much higher mixing efficiency because of its 3-D flow characteristic; the variation of injection angle under circular-hole injection primarily affects the near-field mixing degree, and among the five injection angles studied in the present paper, angle 120 ° is the optimal one; with the increase of the ratio between injector space and diameter, the induced mixing efficiency increase while while causing loss of total pressure can grow greatly; the two-stage injection method designed through reducing the injector area to keep the same hydrogen mass flowrate can induce a much higher mixing efficiency while only a bit larger loss of total pressure when compared to the single-stage injection, and hence the two-stage injection is superior to the single-stage injection. The research results can direct the design of the fuel injection method in the combustor of scramjet engine.