Using the pressure minimum integral, finite element equations are obtained based on the full potential equation.
从全速位方程出发，利用压强极小积分得到有限元方程组。
The conservative full potential equation and C H grid are used to compute the unsteady transonic flows around airfoils and wings.
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。
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。
The transonic flow field around NACA 0012 airfoil is calculated by finite element method from pressure minimum integration, full potential equation being used.
本文采用压强极小积分有限元法计算了NACA 0012翼型的跨音速流场。出发方程为全速位方程。
The transonic flow computation is performed by the use of conservative full-potential equation with exact boundary conditions and the efficient iteration scheme in finite difference method AF2.
跨音速计算采用守恒型金位势方程，精确边界条件和AF 2高效有限差分迭代算法。
The transonic flow computation is performed by the use of conservative full-potential equation with exact boundary conditions and the efficient iteration scheme in finite difference method AF2.
跨音速计算采用守恒型金位势方程，精确边界条件和AF 2高效有限差分迭代算法。
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