实验流体力学Issue(6)：26-31,6.
高超声速锥柱裙模型边界层转捩的弹道靶实验
柳森 1王宗浩 1谢爱民 1陈旭明 1黄洁1
作者信息
- 1. 中国空气动力研究与发展中心，四川 绵阳 621000
- 折叠
摘要
Abstract
To investigate hypersonic boundary transition phenomena and provide reliable experimental data for CFD code validation,boundary layer transition experiments have been con-ducted at the hypervelocity ballistic range of China Aerodynamics Research and Development Center.The cone-cylinder-flare models are 105mm in length,flying at speed of 1.94km/s(Ma 5. 65),with unit Reynolds numbers of 4.32 ×10 7 ~1.20 ×10 8 m-1 .Images of transition and turbu-lent boundary layer are obtained with laser shadowgraph technique,resulting in measured turbu-lent boundary layer thickness of 0.6 ~2.2mm,and the dimension ratio of 0.3 to 0.8 between turbulent eddy and boundary layer thickness,which reduced along the flow direction.It is shown that,images of Ma 5.65 hypersonic boundary layer transition could be obtained by ballistic range experiments at given flight environment,in which the transition location,boundary layer thick-ness and turbulent eddy scale could be determined.关键词
高超声速/边界层转捩/弹道靶/锥柱裙模型/实验Key words
hypersonic/boundary layer transition/ballistic range/cone-cylinder-flare model/experiment分类
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柳森,王宗浩,谢爱民,陈旭明,黄洁..高超声速锥柱裙模型边界层转捩的弹道靶实验[J].实验流体力学,2013,(6):26-31,6.
