Aerodynamic characteristics of airfoil with single plain flap for light airplane wing

A numerical study was performed on a NACA 23012 airfoil with a single plain flap to examine the aerodynamic coefficients at Reynolds number of 3×10
⁶
, and to help for identifying the forces acting on a light airplane wing. Besides, in the paper the flow fields around the airfoil with single plain flap were shown. All calculations were made using a CFD code. For a turbulent model the Spalart-Allmaras method was chosen. Conclusions were made about the aerodynamic efficiency of the proposed configuration wing-single plain flap.