hypersonic

Therefore the dissociation of oxygen should be considered in the case of high temperature or low pressure, especially in the case of hypersonic aircraft.

因此，对应高温和低压，尤其是在高空的飞行器由于环境压力较低的情况需要考虑离解。

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It would reach hypersonic speeds -- five times the speed of sound.

也就是说,要使飞机达到特超音速—即音速的五倍.

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Aerodynamic heating problems are the key to the design of hypersonic vehicle TPS ( Thermal Protection System).

气动加热问题是高超声速飞行器TPS（Thermal Protection System，热防护系统）设计的关键，数值模拟是研究气动加热问题的重要手段，对气动热数值模拟进行研究具有重要的意义。

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The scramjet, which is the propulsion of hypersonic vehicle, has become the focus in many military developed countries.

高超音速飞行器的动力装置&超音速燃烧冲压发动机的研究已成为当前各军事强国研究的热点。

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Cross-section design of a controllable hypersonic inlet. The research is being done at the Nanjing University of Aeronautics and Astronautics.

南京航空航天大学正在进行一个可控高超音速进气道断面设计研究。

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This brief communication introduces an experiment of hypersonic flow using high enthalpy expansion tube.

该研究简报介绍了用膨胀波管产生高超声速气流的实验结果.

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FEM FCT is used to solve three dimensional hypersonic inviscid flow.

从Euler方程 出发,利用流量修正有限元法(FEM?FCT)求解三维无粘流动的高速流场.

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This method combines the robustness of H_ ∞ optimal control theory and non-linear decoupled control ability of the dynamic inversion control well, so it is possible to achieve highly nonlinear decoupled control for hypersonic vehicle and restrain the effects of model parameters change in complicated flight conditions.

该方法将H∞最优控制的鲁棒性能与动态逆控制的非线性解耦控制能力有机结合，能够在复杂的飞行条件下，实现对高超声速飞机高度非线性解耦控制；

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Metallic thermal protection system a feasible solution for thermal protection of hypersonic vehicles.

金属热防护系统是高超飞行器热防护系统的理想候选方案.

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The results of numerical and experimental studies of a new configuration of 3D hypersonic inlet with the minimum throat area, which was called a convergent inlet, are presented in this paper.

介绍一种新型的、具有最小喉道面积的三维高超声速进气道（称之为收敛形进气道）的数值和实验研究结果。

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Integrated thermal protection and control system design methodology for hypersonic vehicles

高超声速飞行器一体化防热与热控设计方法

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Numerical Simulation of Hypersonic Inviscid Flow Around the HERMES Configuration

绕HERMES外形高超声速无粘流动的数值模拟

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Hypersonic aircraft refers to the speed of sound, at least 5 times more than the aircraft.

高超音速飞机是指超过音速至少5倍的飞机.

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Calculation of thermal load and impact factor analysis for hypersonic vehicle

高超声速飞行器热载荷计算及影响因素分析

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Hypersonic wind tunnels operating at very low densities were developed starting in about 1960.

低密度超音速风洞大约开始发展于1960年.

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First, based on the time scale separation theory hypersonic vehicle model is divided into inner and outer loop in order to facilitate controller design.

首先，基于时标分离理论将高超声速声速飞行器模型分解为内外环，以便于控制器设计。

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For the transition prediction for a hypersonic sharp cone or cone with small bluntness, conventional e-N method does not yield correct result, even qualitatively, Then, based on our own previous works, new interpretation and essential improvement for the e-N method is proposed.

对于来流小攻角的锥体边界层，传统的e-N方法即使在定性上也不能给出正确结果。根据我们以前的一些工作，对e-N方法进行了新的诠释，并提出实质上的改进。

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Hypersonic vehicle must be designed in integration methodology for the strong coupling effect of the subsystems.

高超声速飞行器各子系统之间存在着很强的相互作用,这要求在设计过程中必须采用一体化技术.

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With such a large heat sink value, FRA can meet the requirement of hypersonic flying machine.

在800℃时,两者都具有较高的热沉值,分别达到569MJkg和660MJkg, 该热沉值能够满足超高音速飞行器的热管理要求.

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A new method of quickly hypersonic waverider forebody configurations was developed.

发展了一种基于分析法的高超声速乘波构型飞行器前体设计方法.

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The forebody design a key issue for hypersonic airbreathing vehicle.

前体设计是吸气式高超声速飞行器设计的关键之一.

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At supersonic and hypersonic speeds, a shockwave forms around the steak that helps protect it from the faster and faster winds.

在超音速和高超音速条件下，牛排周围会形成激波，而激波会把牛排和越来越快的狂风隔离开来。

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The parabolized stability equations ( PSEs) for high speed flows, especially supersonic and hypersonic flows, are derived and used to analyze the nonparallel boundary layer stability.

针对高速流动，特别是超声速和高超声速流动的非平行边界层稳定性问题进行了研究。

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The development of the larger axial force intermediate temperature balance in the hypersonic wind tunnel

高超声速风洞大轴向力中温天平的研制

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Firstly, stability of a hypersonic boundary layer on a blunt cone with small nose bluntness at zero angle of attack has been investigated and the transition location was predicted by the e-N method.

首先，研究了高超音速零攻角小球头锥边界层的稳定性特点，并用e-N法进行了转捩预测。

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Hypersonic aircraft to fly faster secret lies in its use of a ram-jet engine.

高超音速飞机飞得快的奥秘在于其采用了冲压 式 喷气发动机.

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This paper a brief overview of hypersonic ground simulation equipment status and trend.

本文回顾了高超音速地面模拟设备发展过程.

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The thermal environment of the wedge leading edge is rigorous in hypersonic flow.

高超声速气流条件下，尖楔前缘的热环境非常恶劣。

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An Analytical Solution for Axisymmetric Hypersonic Flow Over a Blunt Nose Body With Sharp Corners Van Chia I

轴对称高超音速绕流具有尖角的钝头体的一个解析解

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Theory of similarity and the profile of the mean density distribution of hypersonic boundary layer

相似理论和高超音速边界层的密度分布

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