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.
高超声速进气道是高超声速吸气式推进系统的重要组成部分，对实现高超声速飞行起着关键作用。
Scramjet inlet is of great importance in the hypersonic airbreathing propulsion system and plays significant role in the realization of hypersonic flight.
超声速进气道的性能优劣决定了补燃室流场内的压强和空气流量，进而影响到冲压发动机的工作性能。
The performance of supersonic inlet determines the pressure and the air flux in combustor, then affect the work of ramjet.
介绍一种新型的、具有最小喉道面积的三维高超声速进气道（称之为收敛形进气道）的数值和实验研究结果。
The results of numerical and experimental studies of a new configuration of 3D hypersonic inlet with the minimum throat area, which was called a convergent inlet, are presented in this paper.
得到了高速旋转工况下对应于不同来流攻角和旋转角速度，临界工况时，超声速进气道内外流场复杂的波系结构。
Complex wave structures of supersonic inlet at different Angle of attack and spinning velocity related to high speed spinning and critical status were achieved.
采用块结构网格与二阶精度流场分区求解技术，对固体火箭冲压发动机增程弹丸超声速进气道特性进行了深入研究。
By means of block structure grid and second-order zonal solver method, the research on supersonic inlet performance of solid rocket ramjet assisted range projectiles was carried out.
超声速进气道的三维流场数值模拟结果与二维数值模拟结果存在较明显的差别，说明进气道侧壁附面层的影响不容忽略；
There is a difference between the numerical simulation results of two-dimensional and three-dimensional flow field in supersonic inlet, which shows the influence of boundary layer on the side wall.
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.
并对超声速段与考虑吸气布局的进气道整体进行了数值模拟，分析了性能。
Take a numerical simulation on supersonic speed segment and the whole part of inlet duct in consideration of air induction placement, analyze its property.
对某冲压增程弹用超声速双锥进气道流场特性进行研究，在风洞试验中得到合理的流场结构图谱及试验数据。
Flow characteristic of supersonic bi-cone inlet of ramjet assisted range projectiles is studied, and reasonable flow structures are also achieved through the wind tunnel experiment.
对于有超声速空气进气道的导弹，导弹弹身和进气道之间存在着复杂的气动干扰，这种干扰难以从理论上进行精确分析。
For a missile with supersonic inlets, there's complicated aerodynamic interference between body and inlets, and this aerodynamic interference is difficulty to analysis in theory.
实验中，自主设计了高超声速直联式风洞模拟自由来流马赫数5.3，通过测量进气道上壁面压力分布，研究了进气道开启过程的起动特性；
During experiment, a directly connected wind tunnel was independently designed to simulate a free stream Mach at 5.3, based on which the dynamic process of inlet opening was studied;
对超声速冲压发动机进气道—喉道段进行了二维稳态流场数值模拟，给出了反压与攻角变化对冲压发动机进气道起动状态影响的数值模拟结果。
The prevailing software numerically simulates a 2-D internal steady flow of the ramjet inlet-isolator; the numerical simulation results of the state of start in the ramjet inlet are presented.
对一种带前体的高超声速矩转圆形进气道开展了数值仿真及高焓脉冲风洞试验研究。
A study is carried out on a hypersonic inlet with rectangular-to-circular shape transition and forebody using numerical simulation and high enthalpy wind tunnel test.
对一种带前体的高超声速矩转圆形进气道开展了数值仿真及高焓脉冲风洞试验研究。
A study is carried out on a hypersonic inlet with rectangular-to-circular shape transition and forebody using numerical simulation and high enthalpy wind tunnel test.
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