Direct Numerical Simulation of Foreign-Gas Film Cooling in Supersonic Boundary-Layer Flow
Direct Numerical Simulation of Foreign-Gas Film Cooling in Supersonic Boundary-Layer Flow
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DOI：
10.2514/1.j055115
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发表时间：
2017
期刊：
影响因子：
2.5
通讯作者：
M. Keller;M. Kloker
中科院分区：
文献类型：
--
作者：
M. Keller;M. Kloker
采用直接数值模拟方法研究了平板上绝热超声速空气主流中的冷却膜特性。空气和氦气被用作冷却气体，并通过单个无限展向狭缝沿壁法线方向以低速率注入层流或湍流附面层流中。通过在没有冷却气体通道的孔口位置（模拟吹制）或在所包括的吹制通道的下端（模拟/相互作用吹制）处规定冷却气体质量通量、质量分数和温度的固定分布来实现吹制，从而允许主流和冷却气体流的相互作用。的影响的建模，主流边界层状态，和冷却气体类型的薄膜冷却的有效性和表面摩擦的变化进行审查;和有价值的数据，用于验证成本较低的计算流体动力学方法采用湍流模型从这个基础研究。
The cooling-film behavior in an adiabatic supersonic air main flow over a flat plate is investigated using direct numerical simulations. Air and helium are employed as cooling gases and are injected with a low rate in the wall-normal direction through a single infinite spanwise slit into the laminar or turbulent boundary-layer flow. The blowing is realized by prescribing a fixed distribution of the cooling-gas mass flux, mass fraction, and temperature at either the orifice location without the cooling-gas channel (modeled blowing) or at the lower end of the included blowing channel (simulated/interacting blowing), thus allowing for an interaction of the main and cooling-gas flows. The influence of the modeling, the main-flow boundary-layer state, and the cooling-gas type on the film-cooling effectiveness and the skin-friction alteration is scrutinized; and valuable data for the validation of less costly computational fluid dynamics methods employing turbulence models are gained from this fundamental study.