Effect of dimples on glancing shock wave turbulent boundary layer interactions

被引：14

作者：

Kontis, K. ^{[1
]}

Lada, C. ^{[1
]}

Zare-Behtash, H. ^{[1
]}

机构：

[1] Univ Manchester, Sch MACE, Manchester, Lancs, England

来源：

SHOCK WAVES | 2008年 / 17卷 / 05期

关键词：

dimples; passive flow control; pressure sensitive paint; transonic and supersonic flows;

D O I：

10.1007/s00193-007-0114-x

中图分类号：

O3 [力学];

学科分类号：

08 ; 0801 ;

摘要：

An experimental study has been conducted to examine the control effectiveness of dimples on the glancing shock wave turbulent boundary layer interaction produced by a series of hemi-cylindrically blunted fins at Mach numbers 0.8 and 1.4, and at angles of sweep 0 degrees, 15 degrees, 30 degrees and 45 degrees. Schlieren photography, oil flow, pressure sensitive paints, and pressure tappings were employed to examine the characteristics of the induced flow field. The passive control technique used a series of 2 mm diameter, 1 mm deep indents drilled across the hemi-cylindrical leading edge at angles 0 degrees, 45 degrees and 90 degrees. The effects of dimples were highly dependent on their orientation relative to the leading edge apex, and the local boundary layer properties.

引用

页码：323 / 335

页数：13

共 28 条

[1] Large-scale roughness influence on turbulent hypersonic boundary layers approaching compression corners [J].