It is further displayed that the testing technique of flexible adaptive walled wind tunnel could apply to future transonic airfoil testing.
实验结果展示了自适应壁风洞实验技术用于翼型跨音速实验的前景。
This paper is a report of experimental pressure. Measurement research for NACA0012 airfoil in NH-1 transonic wind tunnel.
本文为NACA0012翼型在NH - 1风洞进行跨音速二维测压实验的研究报告。
The variational of finite element method(FEM) using the pseudo-potential function is presented to design the airfoil shape of transonic rotational flows.
本文运用赝势函数变域变分有限元方法进行了跨音速翼型设计。
And optimization computation for reducing drag of Shockwave of single airfoil in transonic flow is also successful.
同时进行了单段翼型跨音速降低激波阻力的优化设计。
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 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。
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