1.
The Primary Investigation on Variable Throat and Top Wall of Sidewall Compression Inlet;
喉道顶板可调侧压式进气道初步研究
2.
Numerical simulations of curved surface sidewall compression scramjet inlets with varied sweep angle and sidewall compression angle
变后掠角+变侧压角曲面压缩的高超侧压式进气道数值仿真
3.
Tests and Numerical Simulation on Characteristics of Self-Starting for Sidewall Compression Inlets;
侧压式进气道自起动特性数值模拟和实验研究
4.
Wind tunnel experiment of sidewall compression inlet with adjustable attack angle
攻角动态变化的侧压式进气道风洞实验
5.
Study on back pressure and self-starting characteristics for sidewall-compression inlet with variable internal contraction ratio by moving cowl
移动唇口变收缩比侧压式进气道反压特性和自起动性能
6.
Wind tunnel experiment of the influence of dynamic change of attack angle on start property of sidewall compression scramjet inlet
攻角动态变化对侧压式进气道起动特性影响的风洞试验
7.
Analysis of drags trait in three-dimensional sidewall hypersonic inlet
三维侧压式高超声速进气道阻力特性分析
8.
Experimental Investigation of Fixed-geometry Two-dimensional Mixed-compression Supersonic Inlet with Twin-inlet 90° Configuration at Venter
双下侧定几何二元混压式超声速进气道的风洞试验
9.
Dynamic investigation on hypersonic sidewall compression inlets with cowl valve during the process of transition
带唇口封气活门的高超侧压进气道过渡态工况气动性能
10.
Numerical Simulation of External-Compression Supersonic Inlet Flow Fields
外压式超声速进气道流场的数值模拟
11.
When the relief valve opens, as in the accompanying air-in/water-out diagram, the right-hand channel admits air to the top of the reduced pressure zone, relieving the zone vacuum.
当安全阀开启时，伴随着气进/水出隔膜，右侧渠道使得空气进入减压区顶部，消除减压区的真空。
12.
Investigation of a Two-dimensional Mixed-compression Hypersonic Inlet
一种高超声速二元混压式进气道的研究
13.
Design of a two-dimensional mixed-compression supersonic inlet with boundary layer consideration
考虑附面层影响的二元混压式进气道设计
14.
Influence of blunted-lip cowl on performance of supersonic mixed-compression inlet
钝化唇缘对超声速混压式进气道性能的影响
15.
The numerical simulation of the total pressure distortion in the inlet with flashboard
进气道插板式总压畸变试验的数值模拟
16.
Influence of Boundary Layers Bleed Sew to Start
附面层吸除对二元混压式进气道起动影响分析
17.
Performance and boundary layer of flow in axisymmetric mixed-compression supersonic inlet with cavity
槽对超声速混压式进气道性能及边界层的影响
18.
Design for Throat Length of Mix-Compression Supersonic Inlet with Numerical Analysis
混压式超声速进气道喉道长度的设计与数值研究