The laminar and turbulent compressible boundary layer on a permeable plate under injection of helium in supersonic xenon flow is investigated numerically. The regimes in which the injected gas temperature is lower than the adiabatic impermeable wall temperature are considered. It is shown that at a certain distance from the start of injection the permeable-wall temperature becomes lower than the injected-gas temperature. The regimes of homogeneous injection, when He(5%)–Xe mixture with the Prandtl number Pr = 0.18 is injected, and extraneous injection, when homogeneous helium is injected in a xenon stream, are compared between themselves in the case of the injected-gas or gas-mixture temperatures equal to the adiabatic impermeable wall temperature in the corresponding regime.

中文翻译：

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注入外来气体下超音速流中渗透板传热的显着特征

数值研究了在超音速氙流中注入氦气下渗透板上的层流和湍流可压缩边界层。考虑注入气体温度低于绝热不可渗透壁温的状态。结果表明，在距注入开始一定距离处，渗透壁温度变得低于注入气体温度。当注入普朗特数 Pr = 0.18 的 He(5%)–Xe 混合物时，均质注入的方案和外来注入（当均质氦气注入氙气流时）在注入的情况下相互比较 -气体或气体混合物的温度等于相应状态下的绝热不渗透壁温。