Investigation on transonic round convex-corner flows

被引：2

作者：

Chung, Kung-Ming ^{[1
]}

Chang, Po-Hsiung ^{[2
]}

Chang, Keh-Chin ^{[2
]}

Lu, Frank K. ^{[3
]}

机构：

[1] Natl Cheng Kung Univ, Aerosp Sci & Technol Res Ctr, Tainan 70101, Taiwan

[2] Natl Cheng Kung Univ, Inst Aeronaut & Astronaut, Tainan 70101, Taiwan

[3] Univ Texas Arlington, Aerodynam Res Ctr, Dept Mech & Aerosp Engn, Arlington, TX 76019 USA

来源：

AEROSPACE SCIENCE AND TECHNOLOGY | 2014年 / 37卷

关键词：

Convex curvature; Shock; Boundary-layer separation; Pressure fluctuations; LAYER INTERACTIONS; UNSTEADINESS; MODEL;

D O I：

10.1016/j.ast.2014.05.002

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

Experiments were performed to investigate the flow of a transonic, turbulent boundary layer over regions of sharp and rounded convex surface curvature. The freestream Mach numbers were 0.64, 0.70, 0.83 and 0.89. Test models with three different radii of curvature from 13.7 to 41.7 times the upstream boundary-layer thickness were employed. The total turning angles were 13, 15 and 17 degrees. The flow was found to be accelerated upstream of the curved region. The peak Mach number decreased with increasing radius of curvature for a given turning angle. In comparison with the sharp convex corner, a delay in the transition from subsonic to transonic expansion flows was observed. The shock structure, boundary-layer separation and peak fluctuating pressure were dependent on freestream Mach number, turning angle and radius of curvature. (C) 2014 Elsevier Masson SAS. All rights reserved.

引用

页码：20 / 25

页数：6

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