NUMERICAL PREDICTIONS OF GROUND EFFECT ON NACA OO12
AbstractIn this paper, the CFD package Rampant was used to predict the fluid flow around a NACA 0012 airfoil numerically at varying heights above the ground and at varying angles of attack. These results were then compared with experimental values of lift coefficient and pressure coefficient on the airfoil surface. Only positive angles of attack (with the exception of -4 degrees) were regarded of practical interest in flight and therefore simulated. It has been found a good agreement with the experimental data until a value of 0.5 for the ground distance/airfoil chord ratio. The quality of the obtained prediction is lower for values below 0.5, but in most aeronautical applications we seldom have airfoil/ ground distances below this value.
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