摘要
通过数值分析和风洞实验，研究在非均匀来流条件下，单级斜板型面变化对下游流场的影响。研究结果表明，小进口角，大出口角之凹型面具有较高的总压恢复。但是，曲壁面对降低出口处之静压畸变不利。折衷的选择为：以凹型面作为斜板的前段，其后续一平直段，以达到提高总压恢复，保持较低总静压畸变之目的。
The numerical and experimental study of 2 D compression surface was made under the non uniform supersonic incoming flow. The results of numerical optimization and wind tunnel test show that a best compression surface consists of two segments, the first one is a concave surface with a small entrance angle,the second one is a single wedge. A higher pressure recovery and lower pressure distortion was obtained in Mach 5 3 wind tunnel test.
出处
《推进技术》
EI
CAS
CSCD
北大核心
1999年第4期61-65,共5页
Journal of Propulsion Technology
基金
国家自然科学基本资助
关键词
非均匀流
超声速
进气道
发动机匹配
最优设计
Nonuniform flow,Supersonic inlet,Inlet engine matching,Numerical analysis,Optimum design
