Experimental and Numerical Investigation on 2-D Wing-Ground Interference

The wing collision is a practical aerodynamic problem. All aerodynamics characteristic of the wing are changing in the collision phenomena. In the present project, the collision of 2-D airfoil section with ground will be investigated experimentally and numerically. The study includes a series of wind tunnel experiments to investigate the 2-D wing influence under collision. Numerical simulation by CFD has been carried out using FLUENT software in order to identify the changes of aerodynamics characteristics during the wing collision. The 2-D wing section selected for the study is NACA 4412 airfoil. The investigation has been carried out at different Reynolds Number ranging from (0.1 x 106 to 0.4 x 106), different angles of attack (-40 to 200) and different height above the ground.
Based on take off and landing fly stages the boundary conditions for the experimental and numerical analysis are determined. An experimental set up was designed and constructed to simulate the collision phenomena in a subsonic wind tunnel. The results of the airfoil characteristic are