2차원 날개 주위의 지면효과에 대한 난류 유동장 해석

Abstract

Two dimensional turbulent flow simulations on the low Mach number － high Reynolds number flow about the NACA 4412 airfoil are carried out as the airfoil approaches a ground. It has been turned out that angle of attack between 2 and 8 degrees is recommended for the airfoil to utilize the benefit of ground effect. For the large angle of attack, the increment of lift due to the ground effect is faded away and negative aerodynamic effect such as destabilizing aspect in static longitudinal stability is occurred and the separation point moves to forward as the airfoil approaches a ground.