47th Fluid Dynamics Conference /the 33rd Aerospace Numerical Simulation Symposium (July 2-3, 2015. Institute of Industrial Science , the University of Tokyo), Meguro-ku, Tokyo, Japan
抄録（英）
We calculated flow around a NACA0012 airfoil at angle of attack 7 degrees in Re=30,000 by using Open FORM to investigate a separation bubble on the upper surface side. In Re=30,000, the laminar separation was formed and the flow on the leading edge was affected by a separation bubble. The pressure distribution from the leading edge to 30% chord was constant. The flow on 50% chord reattached to a wing surface. In lower-Reynolds-number (Re=20,000), the pressure distribution on the upper surface was approximately constant from 20% chord to 80% chord. The flow on the trailing edge changed three-dimensionally. The flow field in higher-Reynolds-number (Re=40,000) was similar to the flow field in Re=30,000. We confirmed a difference in the flow on the upper surface by changing of the Reynolds number.
内容記述
形態: カラー図版あり
内容記述（英）
Physical characteristics: Original contains color illustrations
RE=30,000におけるNACA0012翼まわりの流れ場の数値計算
AA1630005011.pdf
(2.38MB)
