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。
The steady hypersonic flow of air over a sphere is studied numerically using CFD-FASTRAN softwares.
利用CFD软件数值模拟高超声速空气绕流球体的层流流场。
Through ground test and hypersonic flow research, he made great progress in air-breathing hypersonic technology.
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。
The results of numerical simulation of the hypersonic flow around a plate with a sharp leading edge are presented.
本文描述绕锐前缘平板高超声速流动的数值模拟结果。
The results showed that the method meets the requirements of sophisticated simulation of supersonic/hypersonic flow.
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。
This paper presents a numerical analysis of inviscid equilibrium and nonequilibrium hypersonic flow past blunt-nosed slender cones.
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。
It's necessary to recognize the different vortices, when aero-optical distortion caused by hypersonic flow is studied using vortex structure as the turbulence model.
利用涡结构对光波通过高速流场的光学传输特性进行建模，就必须进行涡结构的识别。
Numerical methods for hypersonic flow with chemical non-equilibrium reactions on the unstructured grid are used to analyze the drag induction of channel-configurations.
在非结构网格上对二维高超声速化学非平衡粘性绕流进行了数值模拟，并应用此方法对涵道构型高超声速减阻特性进行了数值分析。
Numerical methods for hypersonic flow with chemical non-equilibrium reactions on the unstructured grid are used to analyze the drag induction of channel-configurations.
在非结构网格上对二维高超声速化学非平衡粘性绕流进行了数值模拟 ，并应用此方法对涵道构型高超声速减阻特性进行了数值分析。
An engineering formula for estimating turbulent base heat transfer of hypersonic flow is given on the basis of flight data and the experimental results in shock tunnel.
本文综合飞行数据和激波风洞中的实验结果，给出了一个计算湍流底部热的工程方法。
Based on the piston theory of supersonic flow, the second Lagrange equation is used to set up the dynamic equations of an airfoil with store in the supersonic or hypersonic flow.
基于超音速气动力活塞理论，采用第二类拉格朗日方程建立了带外挂二元翼系统在超音速和超高音速气流作用下的动力学方程。
According to Belotserkovskii's method, using a series expansion and boundary layer method, an analytical solution for axisymmetric 'hypersonic flow over a flat-headed body has been obtained.
根据方法，使用级数展开和附面层方法，得到了轴对称高超音速绕流平头物体的一个解析解。
On the basis of a self-similar solution as well as of the assumption, of the "Transverse Motion", a general linear theory on hypersonic flow over a general slender body is set up in this paper.
本文在平面截面的假定下，以幂次自模拟解为基础，提出了高超音速气流绕一般细长（辶回）转体流动的普遍线性化理论。
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.
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。
A large frame schlieren image technique is presented in the paper. The technique has been applied to visualization of the boundary layer transition on the surface of the cone in the hypersonic flow.
本文介绍了一种大画幅纹影成像技本，应用该技术，显示了高超音速流场中锥体边界层转捩。
The paper widens the application of local method which used to be utilized in rarefied flow to the quick prediction of aerodynamic characteristics of missile-like reentry vehicle in hypersonic flow.
首先，使用局部线性方法给出模型的系数函数的初始估计； 然后使用积分方法，给出它们的积分估计； 进一步，研究这些积分估计的渐近正态性。
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.
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。
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 kind of scan pitot-pressure rake with water cooler was designed in IMCAS for the hypersonic propulsion wind tunnel flow measurement.
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。
In this paper, plasma wake flow of hypersonic reentry vehicle and radar scattering characteristics have been studied.
对再入飞行器等离子体尾迹及其雷达散射特性进行了分析、研究和大量的计算。
This paper presents the results of an experimental study of the unsteady nature of a hypersonic separated turbulent flow.
本文给出高超音速湍流分离不稳定特性的实验研究结果。
This paper presents the results of an experimental study of the unsteady nature of a hypersonic separated turbulent flow.
本文给出高超音速湍流分离不稳定特性的实验研究结果。
应用推荐