实验是在日本室兰工业大学的超声速风洞中完成的。
The experiment was done in the supersonic wind tunnel of Muroran Institute of Technology.
本论文进行了高超声速弹丸的气动热研究。
In this thesis, the aerodynamic heating methods of hypersonic projectile are presented.
为局部超声速区解的稳定，采用人工密度修正。
An artificial density correction is used for the stability on local supersonic region.
对超声速反向射流混合加热方案进行实验验证。
The heating scheme by supersonic counter flow mixing has been tested.
轨迹优化是高超声速滑翔式飞行器关键技术之一。
Trajectory optimization is a key technology of hypersonic glide vehicle.
高超声速气流条件下，尖楔前缘的热环境非常恶劣。
The thermal environment of the wedge leading edge is rigorous in hypersonic flow.
分析了超声速piv系统的硬件及算法应具备的性能。
The performance of hardware and algorithm of supersonic PIV system were analyzed.
建立了基于参数方法的高超声速巡航飞行器MDO模型。
A hypersonic cruise vehicle MDO model based on parametric method is established.
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.
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.
稀薄效应趋于弱化激波等超声速流动结构，物体影响域增大。
Rarefaction effect tends to make supersonic flows move smoothly, and to enlarge the influence domain of cylinder.
实验是在日本室兰工业大学的压力—真空型超声速风洞中进行的。
The experiment was done in the pressure-vacuum supersonic wind tunnel of Muroran Institute of Technology of Japan.
本文采用上述数值算法模拟了超声速扩压器和超声速引射器内流场。
In this paper, the flow field of the supersonic diffuser and the subsonic-supersonic ejector is simulated by numerical method.
首先推导了适用于某第三代超声速战斗机横航向运动方程和传递函数。
Firstly, the directional lateral motion equations and transfer functions suited for the certain third generation fighter were deduced.
轨迹优化是新型高超声速滑翔式再入飞行器方案设计的关键技术之一。
Trajectory optimization is one of the key factors in scheme planning of the new type of hypersonic gliding reentry vehicles.
本文给出钝头细长锥无粘、平衡和非平衡高超声速绕流流场的数值分析。
This paper presents a numerical analysis of inviscid equilibrium and nonequilibrium hypersonic flow past blunt-nosed slender cones.
当激励能量增加，激励器产生的合成射流速度增加，可达到超声速状态；
With the increment of the input energy, the velocity of the synthetic jet could be increased to the supersonic state.
然后设计了超声速气流发生装置并在过冷雾中进行触发冰晶产生的实验。
Then, a supersonic air flow generator for triggering ice crystals generation in supercooled fog is designed.
最后，初步分析了高超声速弹翼表面发生烧蚀后对其外弹道特性的影响。
At last, the effect on the outer ballistic trajectory characteristic after the ablation of hypersonic projectile wing has been analyzed.
吸气式高超声速飞行器是下一代单级入轨和高超声速巡航研究的重点飞行器。
Air-breathing hypersonic vehicle(AHV) has been the next generation single stage to orbit vehicle and hypersonic cruise vehicle.
针对高超声速再入飞行器最远距离滑翔制导关键技术，设计了一种新型制导律。
A novel guidance law is devised for developing the guidance technology of optimal glide of a hypersonic reentry vehicle.
高温非平衡化学反应对高超声速再入飞行器绕流流场的气动热特性有较大影响。
High temperature chemical non equilibrium phenomena have a great effect on the flow field around a reentry vehicle.
本文介绍了高超声速风洞引射器阀门系统采用计算机控制的设计思想和原理框图。
The design concept and principle of injector valve system of hypersonic wind tunnel controlled by the computer are introduced in this paper.
它们的特性依赖于这个非线相互作用势，在此时存在超声速、声速和次声速的孤立子运动。
Its properties depending on the non-linear interaction potentials, there are the supersonic, sonic and subsonic soliton motion in the protein molecules.
超燃冲压发动机是高超声速飞行器理想的动力装置，是当前高超声速技术领域的研究热点。
Scramjet is the perfect propulsive device to hypersonic vehicle, and is a hot issue in current hypersonic technology area.
计算结果与实验结果符合较好，这表明该数值方法是研究超声速引射器的一种重要研究手段。
The calculated results agree well with the test results and it shows that the numerical methods can be used for the study of the supersonic ejector.
高超声速进气道是高超声速吸气式推进系统的重要组成部分，对实现高超声速飞行起着关键作用。
Scramjet inlet is of great importance in the hypersonic airbreathing propulsion system and plays significant role in the realization of hypersonic flight.
高超声速进气道是高超声速吸气式推进系统的重要组成部分，对实现高超声速飞行起着关键作用。
Scramjet inlet is of great importance in the hypersonic airbreathing propulsion system and plays significant role in the realization of hypersonic flight.
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