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首页> 外文期刊>Journal of Spacecraft and Rockets >Aerodynamic Heating Measurement on Afterbody of Hypersonic Flight Experiment
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Aerodynamic Heating Measurement on Afterbody of Hypersonic Flight Experiment

机译：高超音速飞行器尾气气动加热测量

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摘要

Measured aerodynamic heating over the ceramic tile region of the Hypersonic Flight Experiment vehicle was obtained on Feb. 12, 1996. Measurements obtained on this lifting hypersonic vehicle during its suborbital flight at velocities up to 3.88 km/s have been compared with heating correlations. Results of the comparisons of obtained measurements to predictions show good agreement for local-to-stagnation Stanton number ratio. Flight measurements also showed that boundary-layer transition occurred on the windward side and that the position of transition moved forward to a location aft of the nose equal to about 30% of the total vehicle length. Local flow conditions, where transition was observed, are evaluated with a criterion for attachment line transition of a yawed cylinder, and the results show fair agreement providing that the surface roughness effect is taken into account. During flight, relaminarization followed transition along the fore part of the vehicle. This relaminarization is surmised to be due to decreasing Reynolds number along the flight path when the effect of variable entropy, caused by nose bluntness, is accounted for.
机译：1996年2月12日，获得了高超音速飞行实验飞行器瓷砖区域的空气动力学加热测量值。该升速高超音速飞行器在亚轨道飞行过程中以高达3.88 km / s的速度进行了测量，并与加热相关性进行了比较。所得测量值与预测值的比较结果表明，局部到滞止的斯坦顿数比具有很好的一致性。飞行测量还表明，边界层过渡发生在迎风侧，过渡位置向前移动到机鼻后部的位置，大约等于车辆总长的30％。使用偏航圆柱体的附连线过渡准则评估观察到过渡的局部流动条件，并且如果考虑到表面粗糙度影响，则结果显示出合理的一致性。在飞行过程中，再分层沿着飞行器的前部过渡。据推测，这种再分层是由于当考虑到由鼻子钝性引起的可变熵的影响时，沿着飞行路径的雷诺数减少。

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