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Modified over 4 years ago
Meeting Report -Flow Past Airfoils NACA-0012王顥宇
Geometry Use Airfoil NACA-0012 Re=3.24×105 Test:Angles of Attack=6°, 12°, 20°
(1) Angle of Attack=6°
(2) Angle of Attack=12°
(3) Angle of Attack=20°
Drag Coefficient Angles of Attack 6°: 0.033269719 12°: 0.0238165646°: 12°: 20°:
Lift Coefficient Angles of Attack 6°: 0.40094575 12°: 0.579171566°: 12°: 20°:
Pressure Coefficient Angle of Attack=6°
Pressure Coefficient Angle of Attack=12°
Pressure Coefficient Angle of Attack=20°
Aerodynamic Characteristics of Airfoils and wings
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