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- Experiment on Stability for Mixed-Compression Axisymmetric Supersonic Inlet with Fixed-Geometry 定几何混压式轴对称超声速进气道的稳定性实验
- Numerical simulation of compressible and incompressible flows in mix-compression axisymmetric supersonic inlet 超声速进气道可压及不可压流动数值模拟
- Numerical Simulation and Experimental Validation of Flow in Mixed-Compression Axisymmetric Supersonic Inlet with Fixed-Geometry 定几何混压式轴对称超声速进气道气动特性数值仿真和实验验证
- The Blowing-off of the Lip Separation of an Axisymmetric Supersonic Inlet and the Analysis of the Coherence of Dynamic Distortion of the Inlet 超音速轴对称进气道唇口分离流吹除及其动态畸变源相干分析
- Axisymmetric supersonic inlet 超声速轴对称进气道
- Design and Performance Calculation of the Mixed-Compression Fixed-Geometry Axisymmetric Supersonic Inlets 定几何混压式轴对称超声速进气道设计及性能计算
- The numerical simulation of supersonic inlet internal turbulent flow of solid rocket ramjet assisted range projectiles was performed by 2-order implicit TVD. 摘要应用二阶隐式TVD格式对固体火箭冲压发动机增程弹丸超音速进气道内部湍流流场进行了数值仿真。
- Based on the open source code -DUNS for CFD, numerical investigation has been carried out in the thesis to gain an insight into the flow field of a supersonic inlet for pulse detonation engines and the phenomenon of gas mixture detonation. 本文采用数值计算的手段,基于计算流体力学开放源代码DUNS,对脉冲爆震发动机某进气道的内流场和爆震燃烧进行了研究。
- A fixed-geometry two dimensional mixed compression supersonic inlet with sweepforward high-light is tested in a wind tunnel.The inlet is designed in an "X" type missile configuration. 摘要针对一种定几何二元倒置"X"型布局的混压式进气道进行了风洞吹风实验，得到了进气道的性能并进行了分析。
- Modeling approach of supersonic inlet,combustor and variable convergent nozzle were studied respectively by using the small deviation linear theory and piecewise-lumped parameter method. 利用小偏离线性化理论和分段集总参数法,分别研究了超声速进气道、燃烧室和可调收敛喷管的建模方法。
- Unstart boundary is one of the most important issues of supersonic inlets, and also the foundation of inlet protection control. 摘要不起动边界是超声速进气道研究的重要内容，它是进气道保护控制的基础和前提。
- CFD STATUS FOR SUPERSONIC INLET DESIGN SUPPORT CFD在超声速进气道设计上的应用状况
- Matching between supersonic inlet and aero-engine 超声速进气道与发动机的匹配
- two-dimensional supersonic inlet 二元超声速进气道
- Diverterless Supersonic Inlet (DSI) 无隔道超声速进气道
- Ramjet engine is ideal propulsive equipment for new supersonic missile, and supersonic inlets are important components. 冲压发动机是新一代超声速导弹理想的动力装置,超声速空气进气道是它的一个重要部件。
- divertreless supersonic inlet (DSI) 无隔道进气道
- In the paper is given a FORTRAN IV characteristics computer program for the purpose of designing supersonic inlets or calculating its flow field. 本文提供了一种可用来设计、计算超音速进气道的FORTRAN IV特征线法计算机程序，同时对程序采用的数值方法和计算步骤作了 详尽、明了地说明。
- The results show that the unstart boundary of supersonic inlets is mainly concerned with Mach number of freestream without considering the variation of angle of attack. 分析结果表明：在不考虑攻角变化的条件下，进气道不起动边界主要与来流马赫数有关。
- The tide flushed through this narrow inlet. 潮水涌过了狭窄的小湾。
