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