A table-top hypersonic shock tunnel driven by a manually operated shock tube of 29 mm diameter, named Reddy tube, is presented. The shock tunnel is capable of generating hypersonic flow of freestream Mach number 5.5 with a test time of 600 microseconds. Measurement of heat transfer rates for a small model is described. The measured stagnation point heat transfer rates of ～10 W/cm~2 match with the theoretically estimated values within the experimental errors. The simple table-top hypersonic shock tunnel presented here is ideally suited for the class room experiments in the hypersonic aerodynamics course.
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机译：提出了一种台式超音速冲击隧道，该隧道由直径为29毫米的手动冲击管驱动，称为雷迪管。冲击隧道能够以600微秒的测试时间产生自由流马赫数5.5的高超音速流。描述了小型模型的传热速率的测量。实测的停滞点传热率为〜10 W / cm〜2，与实验误差范围内的理论估计值相符。这里展示的简单的台式高超音速冲击通道非常适合高音速空气动力学课程中的课堂实验。
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