سعید جامعی

The physics of flow around a wing is a topic that can be investigated for conceptual design of wing in ground effect. In this study, pressure distribution around a rectangular wing with a NACA 6409 airfoil section, as well as velocity and turbulence distributions in the wake region after trailing of the wing, were numerically examined. Numerical simulations were executed with respect to different angles of attack in ground effect. The flow field in the physical domain around the wing surface was verified with a realizable k-? turbulent model. The numerical results of the rectangular wing were verified with the experimental data from wind tunnel. The flow structures around the rectangular wing had some variation versus the angle of attack. It was predicted that the pressure distribution on the lower surface and the suction effect on the upper surface of the wing were stronger for higher angle of attack. Additionally, the velocity defect and turbulent intensity in the wake region was greater behind the wing at higher angle.