前体边界层状态对高超声速进气道流动结构及性能的影响

蔡巧言; 谭慧俊

前体边界层状态对高超声速进气道流动结构及性能的影响

蔡巧言¹,
谭慧俊²

1.
西北工业大学航空学院, 西安 710072
2.
南京航空航天大学内流研究中心, 南京 210016

基金项目: 自然科学基金(50606017)

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出版历程
- 收稿日期: 2007-04-04
- 修回日期: 2007-07-23
- 刊出日期: 2008-04-28

Effects of the forebody boundary layer state on flow structure and performance of hypersonic inlets

CAI Qiao-yan¹,
TAN Hui-jun²

1.
School of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, China
2.
Internal Flow Research Center, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

摘要

摘要: 采用CFD方法研究了前体边界层状态对轴对称高超声速进气道的波系结构、激波/边界层干扰特性以及流量捕获能力、总压恢复系数等的影响,获得了不同马赫数下进气道性能参数随一级锥边界层强制转捩位置的变化规律,并对采用二维粗糙体作为强制转捩措施给流场所带来的干扰进行了分析,研究中还对比了具体进气道设计方案间的差别.
- 航空、航天推进系统 /
- 高超声速进气道 /
- 前体边界层状态 /
- 强制转捩 /
- 二维粗糙体
Abstract: Influences of the forebody boundary layer state on shock pattern,characteristics of shock/boundary-layer interaction,mass capture capability and total pressure recovery of axisymmetric hypersonic inlet were studied with the aids of CFD.The performance trend in accordance with the forced transition position was obtained at different Mach numbers.As a forced transition device,two-dimensional roughness was introduced to examine the disturbance it made to the flow field.Differences between specific inlet design schemes were also compared in the study.
- aerospace propulsion system /
- hypersonic inlets /
- boundary layer state /
- forced transition /
- two-dimensional roughness

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参考文献(12)

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