Computational Study Of Flow Characteristics Over High Lift Airfoil At Various Angles Of Attack

A numerical simulation aiming to study and investigate flow behavior over a high lift low speed airfoil type AG-16 at various angles of attack ranging from 0 degree to 15 degree and constant Reynolds number “39,709” was performed. Computational fluid dynamic CFD technique was applied to study the flow characteristics around the complicated shape airfoil; for better calculation results and smoother meshing generation process unstructured mesh with tetrahedron grid element was used. SOLIDWORKS program was used for modeling requirements; the modeling process includes designing three-dimensional wing with airfoil cross section AG-16 to take into account the influence of third dimension on the flow variables. The magnitude of adverse pressure gradient and flow separation point was investigated, the critical/stall angle of attack of this type airfoil was specified and the aerodynamic efficiency was studied and analyzed with respect to various angles of attack. The numerical results illustrate that the lift coefficient rise rapidly with decreasing angle of attack. The critical angle of attack that gives the maximum lift was recorded at 14 degree on the other hand the drag increased rapidly at high angles of attack due to flow separation, the optimum angle of attack that provide the maximum aerodynamic ratio was 4 degree.