| Summary: | 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.
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