超燃冲压发动机

非对称来流条件下超燃冲压发动机隔离段气动特性研究

Aerodynamic Performance Analysis of Scramjet Isolator under Asymmetric Supersonic Flow

不同收缩比超燃冲压发动机进气道的数值研究

Computational Study of Contraction Ratio Effects on Scramjet Inlet

MHD能量旁路超燃冲压发动机可行性分析

Feasibility study of MHD energy bypass scramjet

重点介绍了NASALangley研究中心固定几何形状的超燃冲压发动机喷管的气动设计。

It puts emphasis on the aerodynamic de-sign of nozzle of Fixed-Geometry Scramjet at NASA Langley Research Cen-ter .

用FLUENT软件对安装开式壁龛（长深比L/D10）的超燃冲压发动机燃烧室内的高速可压缩流动进行冷态数值模拟，以方便处理试验结果。

Numerical simulation of the inner supersonic compressible flow in a scramjet combustor with open cavities was carried out using FLUENT software to dispose the process of the experimental data .

得出采用乘波体气动布局、双模态超燃冲压发动机以及BTT转弯控制是高超音速飞行器适合的发展方向。

It is hypersonic developing direction that ride wave body aerodynamic configuration , dual-mode scramjet and BTT ( bank to turn ) control scheme .

超燃冲压发动机4Ma进气道试验研究

Mach 4 testing of scramjet inlet model

采用LU隐式方法强耦合求解有限体积法离散的完全N－S方程及组分方程，数值模拟超燃冲压发动机燃烧室内的化学反应流场。

A three-dimensional numerical code has been developed to simulate supersonic reacting flows in scramjet combustor . The code employs an implicit , finite volume , Lower-Upper ( LU ), and time-marching method to solve the complete Navier-Stokes and species equations in a fully coupled and efficient manner .

超燃冲压发动机目前面临的一大难题就是极高的气动力热载荷，燃烧室壁面温度在未经冷却的情况下能达到3000K。这超过了一般结构材料的使用极限。

A major challenge scramjet engines currently faced is the high aerodynamic heat load . The wall temperature of combustion chamber without cooling can reach 3000K , which exceeds the limit of the general material used .

本文采用隐式格式强耦合求解有限体积法离散的考虑化学反应的广义一维Euler方程，数值模拟氢或碳氢燃料超燃冲压发动机燃烧室的化学反应流场。

Global one-dimensional finite volume Euler equations coupled with chemical reactions are implicitly solved to simulate the reacting flowfield of the combustor of Scramjet fueled by hydrogen or hydrocarbon .

超燃冲压发动机煤油燃烧加热器设计中的流场计算

Flow Field Calculation for Designing a Kerosene Heater Used for Scramjet

以超燃冲压发动机为动力的吸气式高超声速飞行器，已成为现阶段的研究热点。

Scramjet-powered air-breathing hypersonic vehicle has become a research focus nowadays .

碳氢燃料超燃冲压发动机点火技术试验

Experimental investigation of ignition technology in liquid hydrocarbon fueled scramjet combustor

超燃冲压发动机燃烧室亚/超燃模态数值研究

Numerical research on subsonic-combustion and supersonic combustion modes in scramjet chamber

超燃冲压发动机燃烧室新型热结构的优化设计

Optimized design on a new type thermal structure of scramjet combustor

超燃冲压发动机燃烧室中双凹腔对引导氢分布的影响

The Influence of Dual-cavity on Pilot Hydrogen Distribution in Scramjet Combustor

超燃冲压发动机磁控进气道设计影响因素分析

Influence Factor Analysis of the MHD Controlled Scramjet Inlet Design

反压对超燃冲压发动机隔离段内流场的影响

Influence of Back Pressure on the Inner Flow Field in Scramjet Isolator

化学非平衡流动对超燃冲压发动机尾喷管性能的影响

Effects of non-equilibrium chemical reaction flow on the performance of scramjet nozzle

超燃冲压发动机一维跨声速流动奇异初值问题

Singular initial value problems of one-dimensional transonic flow in scramjets

在超燃冲压发动机工作过程中，支板前缘的热环境非常恶劣。

The thermal environment of the scramjet strut leading edge is rigorous .

超燃冲压发动机唇口气动热计算研究与分析

Computation and analysis of aeroheating of scramjet inlet cowl lip

基于综合平衡法的超燃冲压发动机燃烧室构型影响分析

Configuration Effect Analysis of Scramjet Combustor Based on the Integral Balanceable Method

论超燃冲压发动机试验研究及其试验设备

Test . In Test On Experimental Studies of Scramjet and Its Test Facilities

超燃冲压发动机由进气道、隔离段、燃烧室和尾喷管组成。

The scramjet is composed of inlet , isolator , combustor and nozzle .

提出了超燃冲压发动机燃烧室的性能分析评价方法。

The methodology for scramjet combustor performance analysis and evaluation is build up .

超燃冲压发动机燃烧室设计计算方法的研究

Analysis of design calculation methods of scramjet combustion chamber

变几何喉道对超燃冲压发动机点火与燃烧性能的影响

Variable geometry effects on the scramjet ignition and combustion

使用液体碳氢燃料的超燃冲压发动机中的雾化是其工作中的一个重要环节，它对提高发动机的性能起着至关重要的作用。

The liquid fuel atomization processes play an important role on scramjet performance .

超燃冲压发动机前体/进气道和隔离段气动设计

On Exploring Design of Hypersonic Forebody / Inlet and Isolator of Integrated Scramjet