尾喷管

尾喷管直接安装在模型发动机的燃烧室出口。

Scramjet nozzle was installed at the exit of the combustor .

发动机和尾喷管匹配引起的跨音振动

Transonic vibration induced by mismatching between engine and thrust nozzle

检查发动机尾喷管无金属颗粒和损坏。

Check the engine tail pipe on metal particles and visible damage .

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 .

这台发动机由一个进气道，一个燃烧室和一个尾喷管组成。

This engine consists of an inlet , a combustor , and a nozzle .

吸气式高超声速飞行器三维后体尾喷管优化设计

3D afterbody nozzle optimization of air-breathing hypersonic vehicle

非对称方形尾喷管内流场数值分析与推力特性研究

Numerical Analysis on Inner Flow Field and Thrust Speciality Research of the Asymmetry Quadrate Nozzle

超燃冲压发动机尾喷管构型参数灵敏度分析

Parametric sensitivity analysis of scramjet nozzle configuration

高超声速飞行器后体/尾喷管一体化设计

The Application of Genetic Algorithms to Afterbody / Nozzle Integrated Design of a Hypersonic Vehicle

计算火箭发动机尾喷管红外特性的封闭腔-净辐射法

Calculation on infrared characteristics of rocket motor nozzle by using enclosed cavity-radiative heat flux method

数值分析带二次流跨音速尾喷管流场

Computation of transonic nozzle with secondary flow

超燃冲压发动机尾喷管设计方法研究

Research on Design of Nozzle in Scramjet

通过发动机系统级模型的仿真实验，验证了尾喷管模型的有效性。

Several system-level models of aircraft engines are assembled to verify the validity of the exhaust nozzle model .

在受试的尾喷管中，收敛扩张喷管增益最大，达24%；

Amongst all tested nozzles , the maximal augmentation of 24 % is attained by a convergent-divergent nozzle .

本文应用简易特征线方法对超燃冲压发动机尾喷管进行了优化设计。

In this thesis , the scramjet nozzle has been designed and optimized by the method of characteristic line .

本研究对具有固定、连续可调进气道和尾喷管的冲压发动机性能进行了计算和比较。

The ramjet performance is calculated and compared with fixed and continuous adjustable structure intake and nozzle in this paper .

计算结果可以用于预测飞机尾喷管高温燃气射流的红外辐射特性。

The algorithm and calculation results could be used to predict the infrared radiant properties of high temperature aircraft nozzle jet .

应用简易特征线方法和粒子群优化算法对尾喷管的优化设计进行了研究。

The design and optimization of the nozzle is researched by use of the method of characteristic line and particle swarm optimization method .

由于高超声速飞行器机体与发动机高度一体化的构型，使超燃冲压发动机尾喷管具有非对称，面罩可调等特点。

The airframe and engine highly integration nature of hypersonic vehicle results in the asymmetry and cowl adjustable characters of the scramjet nozzle .

尾喷管是发动机的重要部件，其连接采用电子束焊接方法，对质量要求很高。

As an important part of engine , the welding quality of the tail pipe should be ensured when jointing it using the electron beam welding .

磁控等离子体对航空发动机尾喷管流动传热的影响吸气式高超声速飞行器三维后体尾喷管优化设计

The Effects of Controlled Plasma by the External Magnetic Field on Fluid Flow and Heat Transfer of Aeroengine Nozzle ; 3D afterbody nozzle optimization of air-breathing hypersonic vehicle

在此基础上建立了一体化超燃冲压发动机进气道、隔离段、燃烧室及尾喷管计算模型，并对一体化设计的超燃冲压发动机模型进行了初步计算。

Based on these efforts , primary calculating models for integrated scramjet engine inlet , separating section , combustion chamber and nozzle were built , and the primarily calculations were conducted .

建立了超燃冲压发动机一体化设计的优化模型，研究了超燃冲压发动机在总体性能要求与约束条件下，进气道、燃烧室（含隔离段）、尾喷管之间的性能匹配和参数优化。

An optimization model was established for integrated scramjet design . Under the condition of integrated design requirement , performance mach and parameters optimization of the inlet / combustor / nozzle were researched .

本文应用最小喷管长度理论对二维超燃冲压发动机尾喷管上壁型线进行了设计，并对尾喷管性能进行了计算，应用粒子群优化算法对所设计的喷管型线进行了优化。

In this thesis , the scramjet nozzle has been designed by the least nozzle length theory . The nozzle characteristic has been calculated . The nozzle line has been optimized by particle swarm optimization method .

以进气道、尾喷管等为代表的复杂终端腔体的电磁散射分析是当前飞行器隐身设计领域的一个热点和难点。

The problem of analyzing scattering from cavity with a complex termination , such as jet inlet and exit of airplane , is one of the most important and challenging topics in the research area of aircraft stealth design .

45°喷管在所有同样填充率条件下都获得了比15°喷管更大的冲量和比冲，这也说明尾喷管压力作用面积对爆轰发动机效能起到了积极的作用。

45 ° nozzles overwhelm 15 ° ones in the impulse and the specific impulse under all filling conditions , which means the area on which pressure can act is one of the key factors of pulse detonation engine efficiency .

本文提出的双轴燃气轮机的局部相似理论，将高压转子看成一台在特定环境下工作的单轴燃气轮机，将高、低压涡轮及尾喷管看成一个独立的联合部件。

Partial similarity of twin spool gas turbine means that the high pressure rotor can be considered as a single spool gas turbine operating under a specifical circumstance , the high and low pressure turbines and exhaust nozzle are considered a single components of a combination .

还计算了一火箭发动机尾喷管的辐射特性，分析了该喷管在中波红外波带2~6μm和长波红外波带8~14μm及全波长的有效辐射和净辐射热流。

Moreover infrared characteristics of a rocket motor nozzl was calculated , and effective and net radiative heat flux of the nozzle in mid-wave infrared band 2 ~ 6 μ m , long-wave infrared band 8 ~ 14 μ m and full wave band were analyzed .

结果说明，引射的冷空气与热主流在双收敛喷管内掺混，确实能降低尾喷管内气流温度、降低红外辐射。

The results for some aeroplanes illustrate that the double convergent walls of the nozzles can intensify the mixing of hot and cold flows , and the violent mixing can greatly reduce the heat radiation flux and the temperature of aeroengine exhaust gas in double convergent nozzles .