1. Meeting Report -Flow Past Airfoils NACA-0012
王顥宇

2. Reference Paper

3. Geometry Use Airfoil NACA-0012 Re=3.24×105 Test:
Angles of Attack=6°, 12°, 20°

4. Grid (25000)

5. (1) Angle of Attack=6°

6. (2) Angle of Attack=12°

7. (3) Angle of Attack=20°

8. Drag Coefficient Angles of Attack 6°: 0.033269719 12°: 0.023816564
6°:
12°:
20°:

9. Lift Coefficient Angles of Attack 6°: 0.40094575 12°: 0.57917156
6°:
12°:
20°:

10. Pressure Coefficient
Angle of Attack=6°

11. Pressure Coefficient
Angle of Attack=12°

12. Pressure Coefficient
Angle of Attack=20°