2D Investigation of a Wing Consept with a NACA 4412 Airfoil in Ground Effect Operation

Abstract

In this study, Lift/Drag and Moment/Lift values of a wing concept with NACA 4412 airfoil under ground-effect conditions were investigated in 2D at varying altitudes. Figure A. Ground effect schematic and pressure distribution around airfoilPurpose: In this study, turbulence modeling of the wing concept designed for a hoverwing operating using ground effect has been made. At varying angles of attack and altitudes, altitude and angle of attack values were tried to be obtained where the maximum lift/drag and minimum moment/lift ratios were the most ideal.Theory and Methods: Analyzes were made using the ANSYS Fluent Academic program. It is made with a realizable k-ε turbulence model at 0 to 10 degrees of attack angles by decreasing by 0.1 chord in each step from 1 chord height to 0.1 chord height. In these analyzes, changes in lift/drag and moment/drag values were observed. Results:The values obtained after the analyzes were compared. It was observed that the maximum lift/drag ratio was obtained at an angle of attack of 4 degrees at an altitude corresponding to 0.1 chord height, and an increase of 38% compared to 1 chord height. Moment/drag, another factor that was taken into account when evaluating the analyzes, showed a remarkable decrease at 0 to 4 degrees of attack angle and changed very little after 4 angles of attack. Conclusion:It was observed that the NACA 4412 airfoil with a length of 2.75 m, which was analyzed, reached the values that it would be both the most efficient and balanced at 4 angles of attack under ground-effect conditions, but wind tunnel experiments were not carried out due to time and financial constraints. In order to make a definite judgment about the analysis results, wind tunnel experiments should definitely be done as a future study.