摘要
本文利用新式的表面热膜系统测量了一组大转折角压气机叶片吸力面附面层的准剪切力分布,系统地研究了不同雷诺数下叶片吸力面边界层的自然转捩过程。试验结果表明:低湍流密度下,转捩区域并不随着雷诺数的改变而变化,雷诺数在3.4×104到8.4×104的范围内,下边界层都是从距离叶片前缘点约40%弦长位置处开始转捩,转捩完成区域位于距离尾缘约30%弦长位置.
The present paper is based on an experimental investigation of a highly-loaded compressor airfoil designed by Pratt＆Whittney at low Reynolds numbers. The experiments have been conducted in a low-speed linear wind tunnel with steady inflow conditions over a range of Reynolds numbers via surface-mounted hot-films. The object of the study is to identify the whole process of natural transition in compressor airfoil. Under steady conditions, the onset and the end of transition are captured by analyzing the quasi-wall shear stress on suction surface at various levels of Reynolds numbers. It was found that there was no significant influence of Reynolds number on the transition process over the airfoil at low free-stream turbulence intensity. The location of transition onset occurs at approximately 40% from the leading edge and transition completion at approximately 30% from trailing edge for all Reynolds number examined.
出处
《工程热物理学报》
EI
CAS
CSCD
北大核心
2008年第3期419-422,共4页
Journal of Engineering Thermophysics
基金
国家自然科学基金(No．50676095，No．50676094)
国防科技创新基金
关键词
表面热膜
Re数
转捩
试验研究
surface-mounted hot film
Reynolds number
transition
experimental investigation
