Experimental and Numerical Investigation on 2-D Wing-Gronnd 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 (-4° to 20°) 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 presented in non-dimensional form as lift, drag and
pitching moment coefficient.