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On-line Access: 2022-06-24
Received: 2021-10-21
Revision Accepted: 2022-01-04
Crosschecked: 2022-06-24
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Citations: Bibtex RefMan EndNote GB/T7714
Shang-cheng XU, Yi WANG, Zhen-guo WANG, Xiao-qiang FAN, Bing XIONG. Design method for hypersonic bump inlet based on transverse pressure gradient[J]. Journal of Zhejiang University Science A,in press.Frontiers of Information Technology & Electronic Engineering,in press.https://doi.org/10.1631/jzus.A2100532 @article{title="Design method for hypersonic bump inlet based on transverse pressure gradient", %0 Journal Article TY - JOUR
基于横向压力梯度的高超声速鼓包进气道设计方法机构:国防科技大学,空天科学学院,中国长沙,410073 目的:在超/高超声速进气道中,横向压力梯度是鼓包对边界层气流产生排移的关键,然而目前基于横向压力梯度的鼓包设计方法还有待进一步发展。本文旨在提出一种横向压力梯度驱动的高超声速鼓包进气道设计方法,以实现鼓包型面上横向压力梯度完全可控。在此基础上分析鼓包对进气道性能的影响,并从流动层面解释其原因。 创新点:1.提出了一种由横向压力梯度驱动的高超声速鼓包进气道设计方法,实现了鼓包与进气道完全一体化的设计;2.明晰了鼓包型面对不起动进气道大尺度分离区的三维重构作用,进而解释了鼓包进气道起动性能改善的原因。 方法:1.通过对鼓包工作原理的分析,提出一种基于横向压力梯度的高超声速鼓包进气道设计方法;2.通过数值仿真,研究鼓包进气道在设计点下对边界层气流的排移效果(图14);3.通过数值仿真和风洞实验相结合的方法,研究鼓包对不起动进气道大尺度分离区的三维重构作用,进而分析鼓包对进气道起动过程的作用机理。 结论:1.采用本文提出的方法实现了由横向压力梯度驱动的鼓包型面设计,且该型面与进气道外压缩面完全一体化;2.在横向压力梯度的作用下,一部分边界层气流被排移出进气道,使得进气道流量系数稍有下降,但总压恢复性能明显提高;3.鼓包型面对不起动状态下的进气道大尺度分离区具有三维重构作用,使得进气道起动性能得到提高;4.采用本文提出的流量修正方法可使鼓包进气道实现全流量捕获。 关键词组: Darkslateblue:Affiliate; Royal Blue:Author; Turquoise:Article
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