基于特征线法，并考虑变比热的影响，开展了高超声速飞行器用单膨胀斜面喷管设计。
For hypersonic vehicles, the effect of nozzle aerodynamic characteristics on vehicles performance is serious.
而高超声速风洞喷管的设计和计算则对解决这一类问题具有重要的科学意义和实用价值。
The design and computation of the hypersonic nozzle have scientific and practical value to solve these problems.
而高超声速风洞喷管的设计和计算则对解决这一类问题具有重要的科学意义和实用价值。
The design and computation of the hypersonic nozzle have scientific and practical value to solve these problems.
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