Airfoil Stall Suppression by Use of Different Types of Bubble Burst Control Plates Placed on NACA 0012 Airfoil
This paper discusses the suppression of the burst of laminar separation bubbles formed on a NACA 0012 airfoil at a stall angle by summarizing the experimental results conducted for this purpose. Wind tunnel tests were made at a chord Reynolds number of 1. 3x105 when two different types of burst control plate with small height were attached inside a short bubble formed on the airfoil. The burst control plates used here are the thin plate type (burst control thin plate) and the rectangular plate type (rectangular cross section burst control plate). Flow visualization tests and surface pressure measurements confirmed that the burst control plate suppresses the bubble burst at a wide range of angle of attack and increases a stall angle and a maximum lift coefficient. PIV measurements were also conducted for the burst control thin plate confirming that the separated and reattaching flow similar to the short bubble formed on the original airfoil is observed when this plate is adequately placed on the airfoil surface.
flow control laminar separation bubble bubble burst stall
Kenichi Rinoie Yasuto Sunada
Department of Aeronautics and Astronautics,University of Tokyo, Tokyo 113-8656,Japan
国际会议
2010 Asia-Pacific International Symposium on Aerospace Technology(2010 亚太航空航天技术研讨会 APISAT 2010)
西安
英文
133-136
2010-09-01（万方平台首次上网日期，不代表论文的发表时间）