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. 63 × 107 to 1. 23×107 per meter, and the angle of attack was 0°. Results indicate that the flow's energy near the plate wall is mainly 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. 5mm and 242. 5mm away from the leading edge of the plate.%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)×107 m 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.
展开▼
