Cl vs Alpha on NACA 0012 PDF

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Cl vs Alpha on NACA 0012 Density-Based Second order upwind

AoA -4 -2 0 2 4 6 8 10 12 14 16 18 20

Velocity X-Velocity Y-Velocity 49.878 -3.488 49.970 -1.745 50.000 0.000 49.970 1.745 49.878 3.488 49.726 5.226 49.513 6.959 49.240 8.682 48.907 10.396 48.515 12.096 48.063 13.782 47.553 15.451 46.985 17.101

Direction Vector X-Vector Y-Vector 3.488 49.878 1.745 49.970 0.000 50.000 -1.745 49.970 -3.488 49.878 -5.226 49.726 -6.959 49.513 -8.682 49.240 -10.396 48.907 -12.096 48.515 -13.782 48.063 -15.451 47.553 -17.101 46.985

Cl -0.445 -0.229 0.000 0.228 0.444 0.641 0.819 0.879 0.861 0.878 0.864 0.885 0.815

AoA vs Cl for NACA0012 1.000

Lift Coefficient (Cl)

0.800 0.600 0.400 0.200 0.000 -5.00

0.00

5.00

10.00

-0.200 -0.400 -0.600

Angle of Attack (Degrees)

15.00

20.00

Pressure-based Solution > Solution Methods > Scheme > Coupled. Gradient > Least Square Cells Based. Pressure > PRESTO! Momentum > Second Order Upwind.

AoA -4 -2 0 2 4 6 8 10 12 14 16 18 20

Velocity X-Velocity Y-Velocity 49.878 -3.488 49.970 -1.745 50.000 0.000 49.970 1.745 49.878 3.488 49.726 5.226 49.513 6.959 49.240 8.682 48.907 10.396 48.515 12.096 48.063 13.782 47.553 15.451 46.985 17.101

Direction Vector X-Vector Y-Vector 3.488 49.878 1.745 49.970 0.000 50.000 -1.745 49.970 -3.488 49.878 -5.226 49.726 -6.959 49.513 -8.682 49.240 -10.396 48.907 -12.096 48.515 -13.782 48.063 -15.451 47.553 -17.101 46.985

Cl -0.4705 -0.2364

0.0000 0.2255 0.4703 0.6985 0.9187 1.1290 1.3226 1.4899

1.6027 1.6335 1.5834

AoA vs Cl for NACA0012

Lift Coefficient (Cl)

2.0000

1.5000

1.0000

0.5000

0.0000 -5.00

0.00

5.00

10.00

-0.5000

-1.0000

Angle of Attack (Degrees)

15.00

20.00...