摘要
针对埋入式进气道进口处吸入了大量的弹身边界层低能流而导致的总压恢复系数较低,出口流场畸变较大的问题,提出了一种基于弹体表面吹气的埋入式进气道流场控制概念,并采用数值仿真先对不带进气道的纯弹身模型进行了边界层控制研究,而后进一步对完整的进气道/弹身模型进行了仿真分析,获得了吹气控制措施对埋入式进气道流动结构和工作性能的影响特性.结果表明:合适的吹气方案确实能够有效地吹除部分弹身边界层,改善埋入式进气道进口前的边界层状况及内通道流态,提高其总压恢复系数并降低出口流场畸变.设计状态下埋入式进气道的总压恢复系数提高了1.5%,畸变指数降低了6.6%.
Due to the large amount of boundary layer ingested into the submerged inlet which results in low total pressure recovery and high flow distortion,a flow control method based on blowing on the fuselage was introduced.By computational method,the models without and with inlet were both studied to obtain the effects of blow technique on the performance and flow structure of submerged inlet.Results indicate that the control method is effective to blow fuselage boundary layer,and improve the boundary layer condition before entrance and the flow in the duct.At the design condition,the total pressure recovery coefficient increased by 1.5% and the distortion index decreased by 6.6% as compared with the baseline case.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2012年第5期1131-1138,共8页
Journal of Aerospace Power
基金
国家自然基金(10802036)
南航青年科技创新基金(NS2010176)
关键词
埋入式进气道
边界层
吹气
总压恢复系数
畸变指数
submerged inlet
boundary layer
blow
total pressure recovery coefficient
distortion coefficient
