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