最后介绍了近无激波机翼修型的工程设计方法。
Finally, an engineering approach for nearly shock-free wing design is introduced.
本文采用全位势方程，在超音速区采用虚拟气体假设，给出了跨音速无激波翼型设计的一种方法。
In this paper, a method for the transonic shock-free airfoil design, based on the full potential equation, using "fictitious gas" assumption, is presented.
本文介绍了可移动式无膜激波管工作原理和在这种新实验设备上进行光学测量的理论依据和实验结果。
In this paper, a set of experiments have been conducted in a movable diaphragmless shock tube, and some experimental data have been obtained.
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