COMPUTATIONAL MODELING OF STEADY AND UNSTEADY LOW SPEED WING IN GROUND EFFECT AERODYNAMICS

Steady and unsteady low speed Wing in Ground (WIG) Effect Aerodynamics as a result if its close proximity to the ground is studied in detail computationally by solving the unsteady incompressible Navier-Stokes equations. WIG effects for both an airfoil and a finite span wing have been carried out and have been validated with experimental data. Behavior of the computed flow patterns and aerodynamic force and moment coefficients has been studied for varying proximity from the ground and compared with published experimental data to assess the quality and reliability of the numerical predictions. A comparative study has also been done to better comprehend and assess the results obtained by using different boundary conditions used to simulate the ground, in order to establish which condition is apt in approximating the boundary layer at the ground during real flight. It is also observed that the trailing vortex system of the wing has a stronger interaction with the ground in the case of a fixed ground. The nature of the interaction of vortex shed from the wing with the ground boundary layer has also been studied for natural vortex shedding at low Reynolds number laminar flow. Formation of a vortex street is observed in the wake region which comprises of alternatively shed vortices of opposite vorticity. The ground effect in the case of a wing attached with high lift devices has also been studied. The case has been calibrated by comparing with experimental data provided by NASA. The ground effect has a significant impact on the flow pattern around the multi element wing, radically effect the pressure distribution profile over the wing.