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所属单位：航空学院

发表刊物：Xibei Gongye Daxue Xuebao

摘要：Prediction of boundary layer transition is important for the design of hypersonic aircrafts. The study of boundary layer transition of hypersonic flow around a flat plate using oil-film interferometry was investigated at Φ500mm traditional hypersonic wind tunnel. In order to measure the skin friction fast and precisely on the hypersonic wind tunnel, the traditional oil-film interferometry technique is improved. A high-speed camera is used to capture the images of fringes and the viscosity of the silicon oil is modified according to the wall temperature measured by thermocouples during the test. The skin frictions of smooth surface and the surface with single square roughness element were measured. For the smooth surface, the boundary layer is laminar. However, the boundary layer transition is promoted by wake vortices induced by the roughness element. Both the results of skin friction with and without the roughness element are in good agreement with the simulation results correspondingly, indicating high accuracy of the oil film interferometry technique. © 2018, Editorial Board of Journal of Northwestern Polytechnical University. All right reserved.

ISSN号：1000-2758

是否译文：否

发表时间：2018-12-01

合写作者：Liu, Shicheng,耿习琴,程克明

通讯作者：董昊