翼型上に生じる層流剥離泡の崩壊制御による失速抑制効果について(境界層・せん断流・遷移(3),一般講演)

概要

論文の詳細を見る
To suppress the burst of laminar separation bubbles formed on a NACA 0012 airfoil at a stall angle, wind tunnel tests were conducted at a chord Reynolds number of 1.3x105 when a thin plate with small height was attached inside a short bubble formed on the airfoil. Flow visualization tests and surface pressure measurements confirmed that the thin plate placed inside the short bubble 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 made and it was revealed 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.
日本流体力学会の論文
2007-08-06