Figure 6. Lift coefficient for NACA0012 in angle of attack α0=10

From

Boundary Element Method Applied to the 2D Foil with Oscillating Heave and Pitch Motions

Mehdi Pourmostafa, Hassan Ghassemi, Parviz Ghadimi

American Journal of Mechanical Engineering. 2020, 8(1), 17-25 doi:10.12691/ajme-8-1-3