MEMS传感器测量平板表面摩擦应力高速风洞试验  

Skin friction measurement of a flat plate in high speed wind tunnel using MEMS sensors

作　　者：梁锦敏[1] 李建强[1] 蒋卫民[1] 李春彦[1] 唐淋伟[1] 田军[1] 

机构地区：[1]中国空气动力研究与发展中心,四川绵阳621000

出　　处：《实验流体力学》2013年第1期1-4,14,共5页Journal of Experiments in Fluid Mechanics

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(Ma)为0.3～0.6,试验雷诺数(Re)为(0.63～1.23)×107m-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。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.

关 键 词：MEMS(微机电系统) 风洞试验 高速风洞 表面摩擦应力 

分 类 号：V211.753[航空宇航科学与技术—航空宇航推进理论与工程]