摘要
针对一种腹下无隔道大偏距S弯进气道,在利用实验结果验证了数值方法的可靠性之后,通过数值模拟分析了该进气道在跨声速段的口面流动特征和内通道二次流特征,解释了声速时性能较高的原因。结果表明:进气道口面设计能够将绝大部分前体边界层低能流扫离进气口;高亚声速和声速时鼓包的静压分布比较相似,而低超声速时则相差较大,这主要由于其形成机理不同;进气道出口截面下方的对涡仍然是由S弯扩压段第2弯的旋流发展而来的。
The flow fields of a ventral diverterless high offset S-shaped inlet at Mach numbers from 0.85 to 1.50 are simulated using a numerical approach which has been validated by experimental data. Results indicate：（1） Most of the boundary layer of forebody is pushed away from the inlet by the design of the inlet aperture;（2） The pressure distributions of the bump surface at high subsonic speed and sonic speed are similar,but at low supersonic speed,the pressure distribution of the Bump surface is different from the previous two because of its different mechanism;（3） The counter-rotating vortices at the lower part of the inlet exit are developed from the counter-rotating vortices formed at the second turn of the S-shaped duct.
出处
《航空学报》
EI
CAS
CSCD
北大核心
2008年第6期1453-1459,共7页
Acta Aeronautica et Astronautica Sinica
基金
国家"973"计划(5130802)
关键词
航空航天推进系统
无隔道
大偏距
跨声速进气道
S弯进气道
二次流
aerospace propulsion system
diverterless inlet
high offset
transonic inlet
S-shaped inlet
secondary flow
