烧蚀冷却对发动机比冲的影响。
Effect of ablative cooling on specific impulse of rocket engine.
隔热层烧蚀冷却、气膜冷却是冲压发动机常用的冷却方式。
Adiabatic ablation cooling, film cooling are the main means and have been used widely.
在冷却剂渗流是一维不可压缩的（或一维定常的）条件下，热层的传热和烧蚀问题可以单独求解。
This paper points out that the thermal and ablative problems of the shield can be solved solely with the coolant flow only under one-dimensional incompressible or steady condition.
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