该方法要求洞壁附近为亚音速流动，但允许模型附近出现超音速区及激波。
The method considers that the flow near tunnel walls is subcritical while the flow near model may be supercritical and shock waves may exist near by model.
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.
指出，当超音速飞行时，在前喷管附近的弹体表面上产生一个局部高压区，由此形成一个翻转力矩。
It is demonstrated that there exists a part of high pressure on the body surface of the rocket near the fore-located nozzles, thus forming a overturning moment.
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