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所属单位：南京航空航天大学航空学院空气动力学系

教研室：高速风洞实验室

发表刊物：Chinese Journal of Aeronautics

刊物所在地：中国航空学会，北京航空航天大学

项目来源：国家自然科学基金

关键字：Boundary layer separation;Compressible flow;Shock train;Oscillating flow;Wind tunnel testing

摘要：The structure and dynamics of an oblique shock train in a duct model are investigated experimentally in a hypersonic wind tunnel. Measurements of the pressure distribution in front of and across the oblique shock train have been taken and the dynamics of upstream propagation of the oblique shock train have been analyzed from the synchronized schlieren imaging with the dynamic pressure measurements. The formation and propagation of the oblique shock train are initiated by the throttling device at the downstream end of the duct model. Multiple reflected shocks,expansion fans and separated flow bubbles exist in the unthrottled flow, causing three adverse-pressure-gradient phases and three favorable-pressure-gradient phases upstream the oblique shock train. The leading edge of the oblique shock train propagates upstream, and translates to be asymmetric with the increase of backpressure. The upstream propagation rate of the oblique shock train increases rapidly when the leading edge of the

论文类型：期刊论文

论文编号：http://dx.doi.org/10.1016/j.cja.2017.02.004

学科门类：工学

一级学科：航空宇航科学与技术

文献类型：J

卷号：30

期号：2

页面范围：663-676

字数：6731

ISSN号：1000-9361

是否译文：否

发表时间：2017-02-14

收录刊物：SCIE