The proximity of a downforce producing wing to the ground has a significant effect on the generation of aerodynamic loads and flow structures. However, a rigid body assumption for the wing may lead to inaccuracies in the estimation of these loads. Static loosely-coupled Fluid-Structure Interaction (FSI) simulations were performed at Reynolds numbers of 4.64·10⁵ and 6.96·10⁵ and ground clearances ranging from 0.053 c to 0.223 c to investigate the effect of deformation in an ABS wing. Results of these simulations demonstrated that wing deflection increased the height at which lift loss occurred, as the reduced wing tip ground clearance led to an earlier main wing vortex breakdown and greater boundary layer separation. The increase in Reynolds number for a constant chord length induced larger variations in critical height: the critical height increased by 0.011 c at Re = 4.64·10⁵ and by 0.021 c at Re = 6.96·10⁵. The larger variation in critical height at the high Reynolds number cases was due to the increase in the magnitude of the aerodynamic loads, and larger deflections.

产生下压力的机翼靠近地面对空气动力载荷和流动结构的产生具有重大影响。但是，机翼的刚体假设可能会导致这些载荷的估计不准确。在4.64·10 ⁵和6.96·10 ^5的雷诺数下进行了静态松散耦合的流固耦合（FSI）模拟。地面间隙为0.053 c至0.223 c，以研究ABS机翼变形的影响。这些模拟结果表明，机翼挠度增加了发生升力损失的高度，因为机翼末端离地间隙的减小导致主翼涡旋破坏更早，边界层分离更大。对于恒定弦长，雷诺数的增加引起临界高度的较大变化：临界高度在Re = 4.64·10 ^5时增加0.011 c，在Re = 6.96·10 ^5时增加0.021 c 。在高雷诺数情况下，临界高度的较大变化是由于气动载荷的大小增加以及挠度变大所致。