提出一个用自适应流线网格计算定常超声速流场的数值方法。
A numerical method of computing steady supersonic flow fields by using adaptive streamline grids.
从近连续流到近自由分子流，计算分析超声速流场的稀薄效应。
Rarefaction effect on supersonic flow fields in the transition from near continuum to near free-molecule flow is analyzed numerically.
本文介绍一种带操纵面机翼的非定常跨声速流的有限差分计算方法。
A numerical method is presented for predicting unsteady transonic aerodynamic flow about aircraft wings with control surface.
实验结果表明：混合过程的总压损失随两种超声速流的密度比、静温比增大而增加。
The experimental results show that the higher the static temperature and the density ratio between two supersonic flow, the more the total pressure losses of flow during mixing.
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.
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.
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.
本文依据三元流动的通用理论，完成了一个跨声速压气机转子流场的准三元迭代计算。
According to the "General Theory of Three-Dimensional flow in Turbomachines", the quasi-three dimensional calculation of the transonic flow field has been achieved for a compressor rotor.
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.
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.
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。
The conservative full potential equation and C H grid are used to compute the unsteady transonic flows around airfoils and wings.
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.
超声速进气道的三维流场数值模拟结果与二维数值模拟结果存在较明显的差别，说明进气道侧壁附面层的影响不容忽略；
There is a difference between the numerical simulation results of two-dimensional and three-dimensional flow field in supersonic inlet, which shows the influence of boundary layer on the side wall.
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.
得到了高速旋转工况下对应于不同来流攻角和旋转角速度，临界工况时，超声速进气道内外流场复杂的波系结构。
Complex wave structures of supersonic inlet at different Angle of attack and spinning velocity related to high speed spinning and critical status were achieved.
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.
采用块结构网格与二阶精度流场分区求解技术，对固体火箭冲压发动机增程弹丸超声速进气道特性进行了深入研究。
By means of block structure grid and second-order zonal solver method, the research on supersonic inlet performance of solid rocket ramjet assisted range projectiles was carried out.
研究了超声速预混可燃气流的温度以及当量比对超声速燃烧流场结构、点火与火焰传播特性的影响。
The effects of temperature and equivalence ratio of supersonic premixed combustible flow on the structure of supersonic combustion flow field, ignition and flame propagation were studied.
在跨声速风洞中研究了声激励对于可压缩流中细长旋成体大迎角流动非对称性的影响效果。
The effect of acoustic excitation on the flow asymmetry over a slender body in compressible flows was investigated in a transonic wind tunnel.
本文采用二维可压缩非定常N-S方程模拟了带有上下开槽壁的跨声速二维管风洞中超临界翼型绕流的流场。
Transonic tube wind tunnel flows over supercritical airfoils with slots on both upper and lower walls have been simulated by using compressible unsteady two dimensional Navier-Stokes equations.
采用纹影系统对超声速可燃气流中的火焰传播进行流场显示。
A schlieren system was used for flow visualization of the flame propagating in a supersonic, combustible flow.
针对各种温度、压力下，马赫数2．5流场中超临界煤油的超声速燃烧性能进行了实验研究。
Characteristics of supersonic combustion by injecting supercritical kerosene fuel into a Mach 2.5 crossflow at various preheat temperatures and pressures were investigated experimentally.
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.
本文定性分析了开式分离的性状，并对钝锥有攻角超声速绕流的开式分离作了数值模拟。
The nature of an open separation has been analysed qualitatively and the numerical simulation has been made for the hypersonic flow with an open separation over the blunt cone at Angle of attack.
超声速进气道的性能优劣决定了补燃室流场内的压强和空气流量，进而影响到冲压发动机的工作性能。
The performance of supersonic inlet determines the pressure and the air flux in combustor, then affect the work of ramjet.
对某冲压增程弹用超声速双锥进气道流场特性进行研究，在风洞试验中得到合理的流场结构图谱及试验数据。
Flow characteristic of supersonic bi-cone inlet of ramjet assisted range projectiles is studied, and reasonable flow structures are also achieved through the wind tunnel experiment.
采用数值分析方法分析了跨声速喷管无粘流动和超声速射流对挡流板的冲击流场。
Numerical analyses of the transonic nozzle inviscid flow and supersonic jet impingement on a jet TAB are presented.
采用低速重复级压气机实验数据，验证了本文所采用的数值方法模拟亚声速压气机流场的精度和可靠性。
The accuracy and realability of the numerical software used to simulate the flow field of subsonic compressor is verified by the experiment data of a certain low speed two stage repeated compressor.
采用低速重复级压气机实验数据，验证了本文所采用的数值方法模拟亚声速压气机流场的精度和可靠性。
The accuracy and realability of the numerical software used to simulate the flow field of subsonic compressor is verified by the experiment data of a certain low speed two stage repeated compressor.
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