Volume 36, Number 6, December 2018
|Page(s)||1156 - 1161|
|Published online||12 March 2019|
Study on Oil-Film Interferometry Measurement Technique of Hypersonic Boundary Layer Transition
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.
Key words: hypersonic / boundary layer transition / oil-film interferometry / skin friction coefficient
关键字 : 高超声速 / 边界层转捩 / 油膜干涉 / 表面摩擦阻力因数
© 2018 Journal of Northwestern Polytechnical University. All rights reserved.
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