| 高超声速圆锥边界层转捩数值研究 |
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| 引用本文： | 刘伟,杨小亮,赵海洋,陈景兵.高超声速圆锥边界层转捩数值研究[J].空气动力学学报,2008,26(4). |
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| 作者姓名： | 刘伟 杨小亮 赵海洋 陈景兵 |
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| 作者单位： | 国防科技大学航天与材料工程学院,湖南长沙,410073 |
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| 基金项目： | 国家重点基础研究发展规划(973计划)
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国家自然科学基金
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| 摘 要： | 以类似于处理湍流脉动的方式来模型化非湍流脉动,考虑湍流的间歇性特征及引起超声速流动失稳机制,研究包括转捩起始位置及转捩区范围的高超声速流动转捩问题,发展可反映扰动模态和可压缩性影响的两方程SST转捩/湍流模式.针对尖锥模型,在马赫数6、攻角O°～2°时,采用第二模态(Second-mode)机制,预测并比较完全层流态、完全湍流态,以及自然转捩发展过程中的表面热流、表面摩阻等气动特性.
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| 关 键 词： | 高超声速 边界层转捩 尖锥 数值模拟 |
Numerical study on hypersonic boundary layer transition over a sharp cone |
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| LIU Wei,YANG Xiao-liang,ZHAO Hai-yang,CHEN Jing-bing.Numerical study on hypersonic boundary layer transition over a sharp cone[J].Acta Aerodynamica Sinica,2008,26(4). |
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| Authors: | LIU Wei YANG Xiao-liang ZHAO Hai-yang CHEN Jing-bing |
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| Institution: | LIU Wei,YANG Xiao-liang,ZHAO Hai-yang,CHEN Jing-bing(College of Aerospace , Meterial Engineering,National Univ.of Defense Technology,Changsha 410073,China) |
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| Abstract: | Treating non-turbulent fluctuations in a turbulence-like manner and considering the intermittency of turbulence and the mechanisms of supersonic flow instability,the hypersonic transition problems that include the transitional onset and transitional extent are studied.Two-equation transition/turbulent SST model,which including the influences of disturbed mode and compressible flow,is also developed.Appling the second-mode mechanism of transition,the aerodynamic characteristics that include skin friction and... |
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| Keywords: | hypersonic flow boundary layer transition sharp cone numerical simulation |
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