Abstract—

Tests were carried in a shock tunnel to determine the heating rate and the wall pressure on a test model flying at hypersonic velocity. The experiments were performed at Mach M = 6.5 and a total enthalpy of 1.2 MJ/kg. Helium was used as the driver gas and air as the driven gas. The effective test time during the tunnel testing was 3.5 ms. The vacuum sputtered gages were used to evaluate the heating rate on the test model. The evaluated heating rate agrees well with numerical simulation. The experimentally measured pressure also agrees with computational fluid dynamics

中文翻译：

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高超声速马赫数细长体的研究

摘要-

在冲击隧道中进行测试，以确定在以超音速飞行的测试模型上的加热速率和壁压力。实验在Mach M = 6.5和总焓为1.2 MJ / kg的条件下进行。氦气用作驱动气体，空气用作驱动气体。隧道测试期间的有效测试时间为3.5毫秒。真空溅射计用于评估测试模型上的加热速率。评估的加热速率与数值模拟非常吻合。实验测得的压力也与计算流体动力学一致