MEMS传感器测量平板表面摩擦应力高速风洞试验 |
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引用本文: | 梁锦敏,李建强,蒋卫民,李春彦,唐淋伟,田军.MEMS传感器测量平板表面摩擦应力高速风洞试验[J].气动实验与测量控制,2013(1):1-4,14. |
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作者姓名: | 梁锦敏 李建强 蒋卫民 李春彦 唐淋伟 田军 |
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作者单位: | 中国空气动力研究与发展中心,四川绵阳621000 |
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摘 要: | 采用两种热敏MEMS传感器阵列和一种电容式MEMS传感器,在FL-21风洞中开展了平板模型表面摩擦应力分布测量试验研究。试验马赫数(地)为0.3-0.6,试验雷诺数(Re)为(0.63-1.23)×10^7m^-1,模型迎角为0°。试验结果表明:平板模型边界层流动能量主要集中在1000Hz以内;试验测得的表面摩擦应力分布随Ma变化规律与可压缩层流/湍流估算值吻合较好;试验所用平板模型边界层流动转捩起始点位于距平板前缘160mm附近,终止点在距平板前缘202.5-242.5mm之间。
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关 键 词: | MEMS(微机电系统) 风洞试验 高速风洞 表面摩擦应力 |
Skin friction measurement of a flat plate in high speed wind tunnel using MEMS sensors |
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Authors: | LIANG Jin-min LI Jian-qiang JIANG Wei-min LI Chun-yan TANG Lin-wei TIAN Jun |
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Institution: | (China Aerodynamics Research and Development Center, Mianyang Sichuan 621000, China) |
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Abstract: | Skin friction distribution test of a flat plate model was conducted using MEMS floating element sensor and two thermal sensitive MEMS-based sensor arrays in FL-21 high speed wind tunnel, and the cross section of its test section is 0. 6m × 0. 6m. The test range of Mach number was from 0.3 to 0.6, the Reynolds number was from 0.63X107 to 1.23×10^7per meter, and the angle of attack was 0°. Results indicate that the flow's energy near the plate wall is main- ly concentrated in the frequency domain less than 1000Hz; the skin friction distribution measured by the MEMS sensors agrees well with the theoretical results during the whole Mach number of the test; the boundary layer transition of the flat plate starts at the point near 160mm, and ends between 202.5ram and 242.5mm away from the leadin~ edge of the plate. |
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Keywords: | MEMS(Microelectro-Mechanical System) wind tunnel test high speed wind tun- nel skin friction |
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