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。
The variational of finite element method(FEM) using the pseudo-potential function is presented to design the airfoil shape of transonic rotational flows.
针对正在建设中的我国第一座增压连续式跨音速翼型风洞（NF-6风洞），提出用虚拟仪器观念和技术来开发风洞智能测控系统的构思和设想，概述了风洞压缩机状态监测与管理系统的软硬件构成。
NF-6 wind tunnel is the first pressurized continuous transonic cryogenic two dimensional wind tunnel in China. The performance of the NF-6 wind tunnel depend up on axial compressor to large extent.
本文运用赝势函数变分有限元方法数值模拟了绕翼型的跨音速有旋流动。
The variation finite element method (FEM) using the pseudo-potential function was presented for the simulation of transonic rotational flows.
增压连续式跨音速风洞在我国尚属首例，是具有国际先进水平的大型高速翼型风洞。
Pressurizing, continuous and transonic wind tunnel is the first one in our country, and it is the world ' s first class tremendous high - speed aerofoil wind.
增压连续式跨音速风洞在我国尚属首例，是具有国际先进水平的大型高速翼型风洞。
Pressurizing, continuous and transonic wind tunnel is the first one in our country, and it is the world's first class tremendous high - speed aerofoil wind.
通过数值求解定常跨音速流的无粘、小扰动方程，根据实心翼型或多孔翼型的边界条件，获得了相应的压力分布。
By numerically solving the inviscid, small disturbance equation in steady transonic regime, with boundary conditions on solid or porous airfoils, the corresponding pressure distribution is obtained.
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。
This paper is a report of experimental pressure. Measurement research for NACA0012 airfoil in NH-1 transonic wind tunnel.
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.
同时进行了单段翼型跨音速降低激波阻力的优化设计。
And optimization computation for reducing drag of Shockwave of single airfoil in transonic flow is also successful.
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。
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。
It is further displayed that the testing technique of flexible adaptive walled wind tunnel could apply to future transonic airfoil testing.
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