Page 1 Meeting Report -Flow Past Airfoils NACA-0012 王顥宇 2009.8.6.Page 2 Reference PaperPage 3 Geometry Use Airfoil NACA-0012 Re=3.24×105 Test: Angles of Attack=6°, 12°, 20°Page 4 Grid (25000)Page 5 (1) Angle of Attack=6°Page 6 (2) Angle of Attack=12°Page 7 (3) Angle of Attack=20°Page 8 Drag Coefficient Angles of Attack 6°: 0.033269719 12°: 0.023816564 20°: 0.024431836Page 9 Lift Coefficient Angles of Attack 6°: 0.40094575 12°: 0.57917156 20°: 0.72841989Page 10 Pressure Coefficient Angle of Attack=6°Page 11 Pressure Coefficient Angle of Attack=12°Page 12 Pressure Coefficient Angle of Attack=20°