TVD格式是目前数值研究以激波为主要特征之一的超声速、高超声速流场的最先进的算法之一。
TVD scheme is one of the most advanced schemes for investigating supersonic and hypersonic complex flows in which shock wave is one of important properties up to date.
乘波体是一种由已知超声速或高超声速流场生成的气动构形，在设计点乘波体构型的整个前缘产成贴附的激波。
A wave rider is a configuration designed such that the bow shock generated by the shape is perfectly attached along the leading edge at the design condition.
在超声速或高超声速绕流中，一种很严重的脉动压力环境是由激波边界层相互作用引起的激波振荡。
One of the more severe fluctuating pressure environments encountered in supersonic or hypersonic flows is the shock wave oscillation driven by interaction of a shock wave with boundary layer.
通过地面试验和高超声速非平衡流的研究，取得了再入突防气动物理的重要进展。
Through ground test and hypersonic flow research, he made great progress in air-breathing hypersonic technology.
作为平均迎角趋于零的特殊情况，本文的数值结果与超声速线化的位流理论是一致的，在高超声速情况与活塞理论一致。
Numerical solutions agree with supersonic linearized potential flow theory as a special case when the mean angle of attack tends to zero and with piston theory in hypersonic case.
笔者自行设计研制了用于高超声速推进风洞流场测量的带有水冷装置的可移动式扫描总压耙。
A kind of scan pitot-pressure rake with water cooler was designed in IMCAS for the hypersonic propulsion wind tunnel flow measurement.
研究结果表明，该方法满足精细求解超声速/高超声速复杂流场要求。
The results showed that the method meets the requirements of sophisticated simulation of supersonic/hypersonic flow.
利用CFD软件数值模拟高超声速空气绕流球体的层流流场。
The steady hypersonic flow of air over a sphere is studied numerically using CFD-FASTRAN softwares.
亚声速气动力采用面源法计算，高超声速气动力采用修正的牛顿流理论计算。
Panel Method was used for subsonic aerodynamic analysis, and the Modified Newtonian Impact Theory was used for hypersonic aerodynamic analysis.
本文提出了一个高超声速非烧蚀钝体尾流全流场的简化模型和简化的空气化学模型。
A simplified flow field model and simple air chemical model for the chemical nonequilibrium wakes of hypersonic non-ablating blunt-body are presented.
通过理论分析、实验测量和数值模拟，研究高超声速粘性相互作用对实验段自由流静压测量的影响。
Hypersonic viscous interaction effects on measurement of free stream pressure in test section are studied through theoretical analysis, experiment measurement and numerical simulation.
对一种轴对称形式的高超声速飞行器全流道开展了风洞实验和数值模拟研究，分析了不同来流总压、飞行攻角全流道的流场结构和气动力特性。
This paper presents a numerical simulation of separated flow over an airfoil at large attack angles with oscillating excitations to study separation flow control over an airfoil.
对偶极子磁场作用下的三维钝头体高超声速黏性绕流的化学非平衡流动进行了数值模拟。
Three-dimensional hypersonic viscous chemical nonequilibrium flows around a blunt body are numerically investigated in a dipole magnetic field.
实验中，自主设计了高超声速直联式风洞模拟自由来流马赫数5.3，通过测量进气道上壁面压力分布，研究了进气道开启过程的起动特性；
During experiment, a directly connected wind tunnel was independently designed to simulate a free stream Mach at 5.3, based on which the dynamic process of inlet opening was studied;
实验中，自主设计了高超声速直联式风洞模拟自由来流马赫数5.3，通过测量进气道上壁面压力分布，研究了进气道开启过程的起动特性；
During experiment, a directly connected wind tunnel was independently designed to simulate a free stream Mach at 5.3, based on which the dynamic process of inlet opening was studied;
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