Skin friction measurements using oil film interferometry and Preston tube at subsonic/transonic regime

Liu Zhiyong; Li Jianqiang; Gao Rongzhao; Tao Yang; Liang Jinmin; Zhang Changfeng

doi:10.11729/syltlx20180032

Volume 32 Issue 5

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Journal of Experiments in Fluid Mechanics > 2018 > 32(5): 76-81. > DOI: 10.11729/syltlx20180032

Liu Zhiyong, Li Jianqiang, Gao Rongzhao, Tao Yang, Liang Jinmin, Zhang Changfeng. Skin friction measurements using oil film interferometry and Preston tube at subsonic/transonic regime[J]. Journal of Experiments in Fluid Mechanics, 2018, 32(5): 76-81. DOI: 10.11729/syltlx20180032

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Skin friction measurements using oil film interferometry and Preston tube at subsonic/transonic regime

High Speed Aerodynamics Institute of China Aerodynamics Research and Development Center, Mianyang Sichuan 621000, China

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Received Date: March 08, 2018
Revised Date: June 26, 2018

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Measurements of skin friction on a flat plate model were conducted in the 0.6m×0.6m subsonic/transonic/supersonic wind tunnel. Oil film interferometry (OFI) and Preston tube technique were applied to obtain the skin friction data at Ma=0.4~0.8. In order to avoid flow separation, an elliptical leading edge was employed. Results indicate that the agreement between OFI and Preston tube is very well. Viscosity of oil film has little influence on the skin friction measurement. When the stream's Mach number or the total pressure changes, the skin friction coefficient decreases along with the increase of the dynamic pressure or the product of Mach number and Reynolds number (Ma·Re). A freckle-like interference pattern was observed at Ma=0.4 and 0.6, and an assumption based on the new pattern was proposed to determine the transition location. According to the oil motion and CFD results, a separation bubble rather than the new pattern appears at Ma=0.8, and it is responsible for the transition of boundary layer.
- OFI,
- Preston tube,
- skin friction,
- transition,
- separation

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