高超声速二维进气道参数化设计方法初探

范晓樯; 李桦; 李晓宇; 丁国昊

高超声速二维进气道参数化设计方法初探

国防科学技术大学航天与材料工程学院, 湖南长沙 410073

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出版历程
- 收稿日期: 2005-12-23
- 修回日期: 2006-06-09
- 刊出日期: 2007-01-28

Preliminary investigation on parametric design method of thetwo dimensional hypersonic inlet

College of Aerospace and Material Engineering, National University of Defense Technology, Changsha 410073, China

摘要

摘要: 通过高超声速二维进气道流动与几何参数制约关系分析和参数敏感性分析, 确定了能够对二维进气道进行参数化设计的5个基本几何控制参数, 初步建立了高超声速二维进气道的参数化设计方法.结果表明该方法选择的基本参数能够敏感地反映进气道的关键性能和尺寸, 为二维进气道型面优化设计提供了切实可行的途径.
- 航空、航天推进系统 /
- 高超声速 /
- 进气道 /
- 优化设计 /
- 参数化设计
Abstract: A parametric design method of the two-dimensional hypersonic inlet was established.By analyzing the restriction and sensitivity of the parameters which affect the inlet performance or configuration,five basic geometric parameters were selected for the parametric inlet design.It is indicated that the key performance and the configuration of the inlet are sensitive to the basic parameters selected.The parametric design method provides a practical way for the optimization design of the two-dimensional inlet.
- aerospace propulsion system /
- hypersonic /
- inlet /
- optimization design /
- parametric design

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参考文献(17)

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