应用隐式AF方法计算了为发动机进气道设计的典型扩压器内的复杂湍流流场。
A complicated turbulent flow field in a diffuser with typical geometric shape for aeroengine inlet design was calculated by the use of the implicit AF method.
以应用于实际设计为目的，研究了现代设计方法在发动机螺旋进气道设计中的应用。
In order to be used in practical design, application of modern design method for engine's helical intake ports is studied.
进行了多方案二元混压超声速进气道设计和筛选，确定了主设计方案，并完成试验研究。
Through many schemes design and filter of 2-D mixed-compression supersonic intake, confirm the design scheme of experimental investation.
该CAD技术与CFD技术的结合能大幅度地缩短埋入式进气道设计周期、降低研制成本。
Combined this CAD technique with CFD, a variety of submerged inlet can be more quickly and more economically designed.
研究开发CA6102型汽油机紊流燃烧系统时，涉及到一些切向进气道设计中的基本问题。
Some fundamental problems in designing the tangential inlet passage are involved when the turbulent combustion system for model CA6102 gasoline engine is researched and developed.
同时说明，在超燃进气道设计过程中，需要充分考虑边界层转捩问题，引入有效的边界层转捩控制方法，以保证发动机的正常工作。
The research coinstantaneous shows that the boundary transition should be considered, and effective transition method should be adopted to ensure the normal work of the scramjet engine.
在此基础上，选择一组口面参数设计了一梯形进口的平面埋入式进气道方案，并进行了高速风洞试验验证。
Then by selecting a group of suitable entrance parameters, a submerged inlet with the trapezoid entrance on the plane surface is designed and verified by wind tunnel tests.
其次是发电机组卓越的特性：分隔开的进气道和排气道设计，避免了空紊流，使得空气循环更加流畅，静音效果更好。
This was followed by the generating units outstanding features: separation of the inlet and exhaust design, to avoid air turbulence, making more air circulation smooth, quiet better.
它可用于指导超音速飞行器的进气道及相关装置的设计。
This work is useful for the design of the inlet and relevant devices in supersonic vehicles.
以汽车发动机螺旋进气道为研究对象，探讨了逆向工程在汽车零部件设计中的应用。
Regarding the helical intake port as a research object, the application of reverse engineering in automobile parts design is discussed.
提供的结果来自飞机进气道的设计和性能研究，分析所用的数据来源于进气道模型风洞实验和CFD数值模拟。
This paaer presents selected results from several investigations of ari inlet design and performance. Diagnodtic data are from airfame-inlet model wind tunnel tests and CFD simulations.
本文介绍了以涡轮喷气发动机为动力装置的飞航式战术导弹的一种新型高亚音速嵌入式、半嵌入式进气道的设计与试验研究结果。
The design and test results of the new type high-subsonic speed submerged and semi-submerged intakes for cruise missile propelled by a turbojet engine have been introduced.
并针对165f结构紧凑的特点，为DI165 F设计适合其特点的短引导管螺旋进气道。
Aimed at 165f structure feature that it is compact, a helical intake port of short lead-channel that suits DI165F is designed.
介绍了柴油机进气道的设计。
以总压恢复系数最大为目标，采用等激波强度和等激波角设计方法建立进气道模型；
The inlet design calculating model was set up based on the theory of equal shock wave intensity and angle of supersonic airflow to get maximum total pressure coefficient.
长期以来进气道的设计主要是依靠气道稳流试验测量其涡流比和流量系数来评定气道的性能。
The design of port is depended on steady flow test to obtain swirl ratio and flow coefficient and use them to evaluate the performance of intake port.
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.
流通进气道的设计，从而使引进的水进入水库切到地表。
The circulation inlet port is designed so as to enable the introduction of water into the reservoir tangentially to the surface.
本文介绍了双斜切进口进气道亚音速管道的设计方法，着重提出了设计中遇到的几个难点和解决办法。
This paper presents a design method of diffuse duct of a Caret inlet, especially focus on several key points and how to resolve them.
以实际产品为研究对象，将三维数值模拟方法应用于柴油机螺旋进气道的改进设计中。
Three-dimensional numerical simulation method is used in the design of a diesel engines helical intake port for the practical product.
论述了飞机进气道可变几何形状控制系统的鲁棒设计方法和系统的综合试验。
A Robust design approach and integrated test procedure of the aircraft variable geometry inlet control system are discussed.
提出了一种尾喷管与进气道整流罩保形设计方案，既保持导弹外形特征不变，又与尾喷管内型面实现一体化保形设计。
A kind of conformal design scheme for tailpipe nozzle and inlet cowl was put forward, which not only keeps missile shape, but also realizes integral conformal design with inner contour of nozzle.
开展了发动机螺旋进气道的三维造型设计的研究。
The 3-d modeling design of engine helical intake port has been studied.
本文尝试采用气动优化设计方法进行进气道的设计。
In this dissertation, Numerical Aerodynamic Optimization method is attempted to apply in the inlet design.
分析了支线民航机一种新型亚音速带有腔室旁通道的进气道的几何形状设计和气动试验结果。
The intake with plenum bypass is a new type subsonic intake for civil medium range aircraft.
有关结论和方法可以为冲压增程炮弹设计提供理论和技术支持，为增程炮弹进气道的设计提供重要依据，对提高其性能非常重要。
The conclusions and method of this paper can be helpful to design the inlet of improved range's cannonball theoretically and technologically.
研究结果表明，当飞行马赫数小于设计马赫数时加速器模式的磁控进气道可以提高进气道的性能。
It can be concluded that the accelerator mode MHD-controlled inlet can improve the inlet performance when the flight Mach number is lower than the design value.
对S型复合材料进气道进行了铺层结构设计与分析。
Fiber placement layers of s inlet duct are designed and analyzed by request of design.
对S型复合材料进气道进行了铺层结构设计与分析。
Fiber placement layers of s inlet duct are designed and analyzed by request of design.
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