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Abstract：
This study explores the efficacy of dimples in influencing the aerodynamic performance of a straight rectangular wing. Computational Fluid Dynamics based numerical simulations were performed to model turbulent flow and quantify the forces exerted on the wing. The k-ω Shear-Stress Transport turbulence model was chosen to solve the underlying equations. To ascertain reliability, the results of numerical simulations were compared with both experimental and simulation results of the previous studies. The impact of various dimple configurations, placed at 15%, 50% and 85% of the chord length, on the aerodynamic performance of the wing was investigated. The evaluation involved analyzing the drag coefficient (CD), lift coefficient (CL), lift-to-drag (L/D) ratio, streamlines and the flow field around wing in both chordwise and spanwise directions. The findings indicated that a wing with a dimpled surface could yield a reduced drag coefficient of up to 6.6% compared to the unmodified wing. This reduction is attributed to the dimples ability to sustain attached airflow and delay flow separation. The results demonstrated negligible deviation in the lift coefficient with the incorporation of dimples. The incorporation of dimples on the wing surface has been demonstrated to enhance the aerodynamic performance of lifting surfaces.
摘要：
本研究探讨了凹坑对直矩形机翼气动性能的影响。进行了基于计算流体动力学的数值模拟，以模拟湍流并量化施加在机翼上的力。选择k-ω剪切应力传输湍流模型来求解基础方程。为了确定可靠性，将数值模拟的结果与以往研究的实验和模拟结果进行了比较。各种凹坑配置的影响，放在15%，50%和85%的弦长，对机翼的气动性能进行了研究。评估涉及分析阻力系数(CD)，升力系数(CL)，升阻比(L/D),翼弦向和翼展方向的流线和机翼周围的流场。研究结果表明，与未修改的机翼相比，具有凹痕表面的机翼可以降低高达6.6％的阻力系数。这种减少归因于凹坑维持附着的气流和延迟流分离的能力。结果表明，在引入凹坑的情况下，升力系数的偏差可忽略不计。已证明在机翼表面上引入凹坑可以增强升力表面的空气动力学性能。
