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在跨音速马赫数范围内需要经验结果。Empirical results are needed in the transonic Mach regime.

在跨音速马赫数范围内需要经验结果。Empirical results are needed in the transonic mach regime.

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目的优选人参总皂苷的超声波提取工艺。Objective To optimize the transonic -extraction process of Radix ginseng.

提出了一种有效的跨音速翼型气动优化设计方法。An effective aerodynamic optimization design method of transonic airfoil is given.

本文提出了求解跨音速欧拉方程的一种隐式时间推进法。An implicit time-marching method is presented for solving the transonic Euler equations.

本文介绍机翼跨音速定常无粘绕流的一种数值计算方法。A numerical Calculating method of inviscid steady transonic flow over wings is presented.

因此，它在跨声速和超声速流的实验研究中得以广泛地应用。Thus it was extensively applied to experimental research of transonic and hypersonic flow.

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本文提出一种新的定常无粘跨音速流动的有限元计算方法——守恒型有限元素法。A new finite element algorithm for computing steady transonic flows is presented in this report.

本文采用迭代求解的方法计算弹性机翼的跨音速压强分布。An iteration method is used for computing the transonic pressure distribution on a flexible wing.

在亚跨超CFD软件平台中，提供了一个网格生成平台。A grid generation platform is provided in subsonic, transonic and supersonic CFD software platform.

耦合结构动力学方程，建立了基于状态空间的跨声速气动弹性分析模型。Coupled with the structural equations, the models for transonic aeroelasticity in state-space are got.

使用跨音速非定常空气动力，对扑动间隙和旋转间隙进行研究。Flapping and rotary gap have been investigated with the help of transonic unsteady aerodynamic forces.

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在低展弦比、低轮毂比的轴流压气机中激波结构常常是三维的。The shock structure in a transonic compressor with the low aspect ratio of blading is three dimensional.

采用任意中弧线叶片造型程序，将某单级跨声、常规设计的风扇改进为复合掠形设计。An arbitrary airfoils blade design procedure was adopted to redesign a transonic fan with compound swept.

本文介绍机翼无粘定常跨音速绕流的一种数值计算方法。A numerical method for calculating steady inviscid transonic flows over wings is introduced in this paper.

对叶尖段进行跨音修正，对根部应用叶栅最佳损失攻角加以考虑。Some corrections have been made to transonic portion of the blade and large solidity cascade portion at hub.

为论证方法的有效性，给出了几个跨音速涡轮叶栅的计算结果。Several computed results of transonic turbine cascades are presented to illustrate the method's capabilities.

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在低亚音速范围，后体阻力基本不变化，随着马赫数增加至跨音速，出现激波阻力。The drag of aftbody keeps constant in low subsonic flow, but increases in transonic flow due to the shock wave.

本文对二维非结构网格无粘流场计算的多重网格方法作了探讨。Two dimensional transonic flows are simulated by solving Euler equations with finite volume method numerically.

对M6机翼跨音速有升力情况进行了计算，其结果与实验值符合较好。The numerical results of M6 wing in transonic flow are presented, which show that the present method is efficient.