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.
采用C-H型网格、守恒型非定常全位势方程的时间精确近似因式分解差分法计算二维、三维的跨声速非定常位势流。
The conservative full potential equation and C H grid are used to compute the unsteady transonic flows around airfoils and wings.
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