Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)
University of Tokyo
Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)
Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)
Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)
43rd Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2011 (July 7-8, 2011. Waseda University, International Conference Center), Tokyo Japan
抄録（英）
In this study, aerodynamic characteristics of Ishii airfoil at Reynolds number 23,000 are evaluated by large-eddy simulation. For the computational analysis, sixth-order compact scheme for spatial differencing and second-order backward differencing for temporal integration are adopted. The results show that flow around Ishii airfoil has trailing edge separation at low angles of attack, it has leading edge separation and reattachment at medium angles of attack, and it has only leading edge separation at high angle of attack. This characteristics is almost the same as that of NACA0012 which is previously studied. However, the airfoil characteristics of Ishii airfoil are much better than those of NACA0012. This is because of both enhancement in lift by pressure side camber and reduction in drag by pressure side shape.
内容記述
形態: カラー図版あり
内容記述（英）
Physical characteristics: Original contains color illustrations
LESによる石井翼(Re=23,000)の空力特性評価
65207008.pdf
(1.51MB)
