摘要
为研究高超声速边界层转捩现象、给边界层计算提供可靠的对比数据，在中国空气动力研究与发展中心趟高速弹道靶上开展了锥柱裙模型高超声速边界层转捩的自由飞实验。所采用的锥柱裙模型全长105mm，飞行速度1．94km／s（Ma=5．65），单位雷诺数4．32×10^7～1．20×10^8m-1。使用激光阴影成像技术，获得了锥柱裙模型边界层转捩和湍流边界层发展的图像，测得的湍流边界层厚度在0．6～2．2mm之间，湍流涡的流向尺寸与边界层厚度的比值介于0．3～0．8之间且沿流向呈下降趋势。实验结果表明：弹道靶实验能够获得给定飞行环境下的高超声速边界层转捩图像，从图像中可以清晰判断转捩位置或区域、测量边界层厚度和分析湍流涡的尺寸。
To investigate hypersonic boundary transition phenomena and provide reliable experimental data for CFI） code validation,boundary layer transition experiments have been con- ducted at the hypervelocity ballistic range of China Aerodynamics Research and Development （＇enter. The cone-cylinder-flare models are 105mm in length, flying at speed of 1.94km/s（Ma5. 65）,with unit Reynolds numbers of 4.32×107 -1.20×10^8m-1 Images of transition and turbu- lent boundary layer are obtained with laser shadowgraph technique, resulting in measured turbu- lent boundary layer thickness of 0.6~2.2ram, 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 Ma5.65 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.
出处
《实验流体力学》
CAS
CSCD
北大核心
2013年第6期26-31,共6页
Journal of Experiments in Fluid Mechanics
关键词
高超声速
边界层转捩
弹道靶
锥柱裙模型
实验
hypersonic
boundary layer transition
ballistic range
cone-cylinder-flare model
experiment
