By using results obtained in tests on supersonic combustion of hydrogen in air, the conditions governing model size and operating pressure levels for shock tunnel experiments on models of flight vehicles with scramjet propulsion are established. It is seen that large models are required. The development of the stress wave force balance is then described, and its use as a method of measuring thrust/drag on such models is discussed. Test results on a simple, fully integrated scramjet model, with intakes, combustion chambers, thrust surfaces and exterior surfaces, using a 13% silane 87% hydrogen fuel mixture, showed that a steady state with thrust generation could be achieved within the shock tunnel test time, and the thrust could be measured. Results are presented for a range of stagnation enthalpies, and show that the scramjet model produces net positive thrust at velocities up to 2.4 km/sec.
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机译：通过利用在空气中氢的超声燃烧测试中获得的结果，建立了控制模型尺寸和操作压力水平的条件，该条件用于在具有超燃冲压推进器的飞行器模型上进行冲击隧道实验。可以看出，需要大型模型。然后描述了应力波力平衡的发展，并讨论了其在这种模型上作为测量推力/阻力的方法的用途。在简单，完全集成的超燃冲压发动机模型上的测试结果（使用进气口，燃烧室，推力表面和外表面，使用13％的硅烷和87％的氢燃料混合物）表明，在冲击隧道测试中可以达到稳态并产生推力时间，推力可以测量。给出了一系列停滞焓的结果，并表明超燃冲压发动机模型在高达2.4 km / sec的速度下产生净正推力。
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