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

Angles of Attack

6°: 0.40094575

12°: 0.57917156

20°: 0.72841989

Pressure Coefficient

Angle of Attack=6°

Pressure Coefficient

Angle of Attack=12°

Pressure Coefficient

Angle of Attack=20°