Computational Analysis on Aerodynamics of the Airfoil in Ground Effect

Aerodynamic characteristics of an airfoil NACA4412 in ground effect are investigated with the numerical simulation method. The N-S equations and the Spalart-Allmaras model are solved by the finite volume method in CFD software. This paper computes the velocity and pressure distributions under different clearances and angles of attack. Compared with the experimental results, it indicates this computational model is appropriate and the results of computations show the lift coefficient, drag coefficient and lift-drag ratio curves under different clearances and angles of attack.