The uniform design and response surface methodology(RSM) are applied to the multi-objective optimization of a 2-D mixed compression scramjet inlet.
基于响应面法进行了二维混合压缩超燃冲压发动机进气道的多目标优化研究。
Scramjet inlet is of great importance in the hypersonic airbreathing propulsion system and plays significant role in the realization of hypersonic flight.
高超声速进气道是高超声速吸气式推进系统的重要组成部分，对实现高超声速飞行起着关键作用。
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