Reynolds-averaged Navier–Stokes and wall–modelled large–eddy simulations of sonic hydrogen injection into hypersonic crossflow

The combustion efficiency in supersonic combustion ramjets (scramjets) is strongly dependent on the fuel injection process. This paper investigates the transverse injection of hydrogen into a hypersonic air crossflow at Mach 6 . The flow physics are investigated using both Reynolds-averaged Navier-Stokes (RANS) simulations and wall-modelled large-eddy simulations (WMLES). We focus on the comparison of the results of these two methods and their agreement with experimental temperature measurements. Assessing the performance of RANS and its shortcomings in this context is of particular interest due to its significantly reduced computational costs and its widespread use in the hypersonics community compared to WMLES