Numerical methods are used to study the aerodynamic characteristics of different airfoils in ground effect at subsonic velocity. Taking Ma as 0.5 as the flow condition, the effects of airfoil parameters and flight height on aerodynamic characteristics are studied. The calculation results show that in the case of ground effect with Ma of 0.5 and angle of attack of 6°, reducing the airfoil curvature is easier to generate shock wave drag at the leading edge of the airfoil. Increasing the trailing edge curvature of the lower surface will increase the pressure on the trailing edge, the lift coefficient and the nose down pitching moment increase accordingly. As the flying height decreases, the ground effect enhances, the pressure on the lower surface of the airfoil increases, and the lift increase on the lower surface is greater than the suction loss on the upper surface. The wing lift coefficient and lift-to-drag ratio increase more and more significantly.