Figure 10. Pressure coefficient distributions (𝐶p) at angles of attack, α = 10°, 14°, and 16° for the baseline, SETE 20%c, and GF 2%c under steady and unsteady flow

From

Numerical Investigation of a NACA 0012 Airfoil with Static-Extended Trailing Edges and Gurney Flaps for Low-Reynolds-Number Wind Turbine Applications

Tiberius S. Gikenyi, Churchill O. Saoke, Joseph N. Kamau

American Journal of Energy Research. 2025, 13(3), 86-95 doi:10.12691/ajer-13-3-2