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.
高超声速飞行器的设计工具，即地面试验、计算和飞行试验，在模拟高超声速飞行方面都有其局限性。
The developing tools for hypersonic vehicle, i. e. ground test, computation and flight lest all have limitations for simulating 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.
故此，英勇的小羊从南极的大气层以超声速飞来，并用一个综合的光电策略观纠正了他们。
So the heroic lamb flies from the atmosphere Antarctic at a supersonic speed, who then corrects them with a photoelectric lactic synthetically.
本文首次将底部排气法应用于导弹上，结合一种具有常规气动布局的超声速导弹进行了底部排气方案设计，采用一种“底窝器”来提高进气道整流罩的底部压强，并进行了风洞实验验证。
Then, the base bleed method is introduced on a general supersonic missile to decrease the base drag of the inlet cowl for the first time and is validated by wind tunnel test.
“升力推力”飞行器是根据新世纪对高超声速飞行器的需求提出的一种新型飞行器概念，它可以使飞行器的升阻比得以有效提高。
This paper made some analysis on techniques of the concept and power for the "lift-thrust" aircraft, and looked into its future development.
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.
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.
故此，英勇的小羊从南极的大气层以超声速飞来，并用一个综合的光电策略观纠正了他们。
So the heroic lamb flies from the atmosphere of Antarctic at a supersonic speed, who then corrects them with a photoelectric tactics synthetically.
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.
火焰的高超声速速度缩短了粉末与火焰之间的相互作用时间，而火焰也促使了颗粒增长和涂层分解的低温限制。
The hypersonic velocity of the flame shortens the time of interaction between the powder and flame, while the low temperature of flame limits the grain growth and decomposition of coating.
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.
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.
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.
基于此，介绍了基于激波风洞的超声速磁流体动力技术实验系统的基本组成、设计思想和调试情况。
In this paper, basic composition, design methods, and debugging situation of a supersonic MHD technical experimental system based on shock tunnel are introduced.
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.
采用后向面判别法和深度缓冲器算法分析面元之间的遮挡关系，计算了整个高超声速飞行器的RCS。
To compute RCS of whole HCV, the shadowing relationship of facet analyzed by the method of backward surface identification and depth-buffer is considered.
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.
分布参数控制体系的新原理、方法、实现手段将对高超声速发动机系统的运行和设计产生重要影响。
The new principles and methods of distributed parameter control may have an impact on the operation and design of hypersonic jets.
依据钝锥体再入远尾迹流动的边界层特征，从边界层方程出发得到了高超声速远尾迹流动的拟相似性解。
According to the boundary layer character in reentry wake of hypersonic blunt cone body, this paper presents a local similar solution for hypersonic wake.
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.
而高超声速风洞喷管的设计和计算则对解决这一类问题具有重要的科学意义和实用价值。
The design and computation of the hypersonic nozzle have scientific and practical value to solve these problems.
通过对多个复杂超声速横侧射流工况的计算，验证了新模型的预测效果。
Several complex supersonic transverse injection flows were calculated to verify the performance of the new model.
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.
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.
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.
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