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首页> 外文期刊>Experimental Thermal and Fluid Science: International Journal of Experimental Heat Transfer, Thermodynamics, and Fluid Mechanics >Hypersonic shock-wave/boundary-layer interactions on a cone/flare
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Hypersonic shock-wave/boundary-layer interactions on a cone/flare

机译：锥形/闪光上的高超声声冲击波/边界层相互作用

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摘要

Time-resolved surface temperature measurements have been carried out on a 7 degrees half-angle circular cone/flay model in the Air Force Research Laboratory's Mach-6 Ludwieg Tube using infrared thermography. Measurements were performed at zero angle of attack on a total of 16 different nose bluntness/flare angle geometries at three different freestream unit Reynolds numbers. The boundary layer entering the interaction region was turbulent for the two sharper nosetips and laminar for the two blunter nosetips. Stanton-number contours and profiles were used to investigate the effect of nose bluntness, flare angle, and freestream unit Reynolds number on the length of boundary-layer separation and the peak heating achieved upon reattachment. The classical scaling analyses of Souverein et al. and Hung & Barnett for separation length and peak heating, respectively, have been extended for the use of axisymmetric cone/flare shock-wave/boundary-layer interactions. Scaling the peak heating with the density ratio across the separation shock wave, instead of the pressure ratio, significantly improves/simplifies the analysis.
机译：使用红外热成像，在空气研究实验室的Mach-6 Ludwieg管中的7摄氏半角圆锥/剥离模型上进行了时间分辨的表面温度测量。在三个不同的FreeStream单元Reynolds号码中，在零攻角以零攻角进行测量。进入相互作用区域的边界层对于两个持续的镍氢滴度和层流是湍流的两个通风机Noosetips。斯坦顿数轮廓和型材用于研究鼻子钝性，喇叭角和自由流动单元雷诺数对边界层分离的长度和在重新附着时达到的峰加热的影响。 Souverein等人的经典缩放分析。分别用于分离长度和峰值加热的Hung＆Barnett用于使用轴对称锥/眩光冲击波/边界层相互作用。将峰值加热与分离冲击波的密度比例进行缩放，而不是压力比，显着改善/简化了分析。

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