On the observation of biomimetic Humpback Whale (HW) flippers, the airfoil aerodynamic performance characteristics are explored. The Leading Edge (LE) tubercle geometry was inspired by the flipper of HW that has rounded LE protuberances and tapered trailing edge configurations. The tubercles have excellent flow control characteristics at the post-stall region. Aerodynamic characteristics of airfoils such as NACA0015 and NACA4415 with LE tubercles are experimentally and numerically investigated at the low Reynolds number about Re = 1.83 × 10⁵. The bio-inspired modified airfoils (HUMP 0015 and 4415) are designed with the amplitude to wavelength ratio (η)$\left(\eta \right)$$\left(\eta \right)$ of 0.05. The numerical simulation over the modified airfoils shows that, at higher Angle of Attack the flow separation is delayed in the peak region whereas the early flow separation is observed in the trough region adjacent to the LE. The boundary layer flow separation analysis is done extensively through numerical simulations and the velocity vector profiles are captured at different chordwise positions. The stall delay phenomenon is observed through the outcome of this research that specifically insists at the peak region of tubercles. Computation of Coefficient of pressure (Cp)$\left({\text{C}}_{\text{p}}\right)$$\left({\text{C}}_{\text{p}}\right)$ distribution is also done by both numerical and wind tunnel experiments. Analysis of Cp${\text{C}}_{\text{p}}$${\text{C}}_{\text{p}}$ distribution allows the identification of critical regions that initiate the adverse pressure gradient and region of flow separation. It is a novel effort to predict the Coefficients of Lift (CL)$\left(C_L\right)$$\left(C_L\right)$ and Drag (CD)$\left(C_D\right)$$\left(C_D\right)$ concerning the bio-inspired airfoils through Cp${\text{C}}_{\text{p}}$${\text{C}}_{\text{p}}$ distribution such that the influence of flow separation and vortex distribution are characterized for the modified and baseline airfoils. Comparison of Cp${\text{C}}_{\text{p}}$${\text{C}}_{\text{p}}$, CL$C_L$$C_L$, and CD$C_D$$C_D$ between the baseline and modified airfoils reveal the enhanced momentum transfer characteristics of bio-inspired tubercles.

通过对仿生座头鲸（HW）鳍状肢的观察，探讨了翼型气动性能特征。前缘 (LE) 结节几何形状的灵感来自于具有圆形 LE 突起和锥形后缘配置的 HW 鳍状肢。结节在后失速区域具有出色的流量控制特性。在大约Re = 1.83 × 10 ⁵的低雷诺数下，对带有 LE 结节的 NACA0015 和 NACA4415 等翼型的空气动力学特性进行了实验和数值研究。仿生改进翼型（HUMP 0015 和 4415）的设计具有振幅与波长的比值( η)$\left(\eta \right)$$\left(\eta \right)$0.05。对改进翼型的数值模拟表明，在更高的攻角下，峰值区域的流动分离延迟，而在靠近 LE 的波谷区域观察到早期的流动分离。边界层流动分离分析通过数值模拟广泛完成，速度矢量剖面在不同的弦向位置捕获。通过这项特别坚持在结节高峰区域的研究结果观察到失速延迟现象。压力系数的计算(Cp)$\left({\text{C}}_{\text{p}}\right)$$\left({\text{C}}_{\text{p}}\right)$分布也通过数值和风洞实验完成。分析Cp${\text{C}}_{\text{p}}$${\text{C}}_{\text{p}}$分布允许识别引发逆压梯度的关键区域和流动分离区域。这是一项预测升力系数的新尝试(C大号)$\left(C_{\mathrm{大号}}\right)$$\left(C_L\right)$并拖动(CD)$\left(C_D\right)$$\left(C_D\right)$关于仿生翼型通过Cp${\text{C}}_{\text{p}}$${\text{C}}_{\text{p}}$分布使得流动分离和涡流分布的影响被表征为修改和基线翼型。相对比Cp${\text{C}}_{\text{p}}$${\text{C}}_{\text{p}}$,C大号$C_{\mathrm{大号}}$$C_L$， 和CD$C_D$$C_D$在基线和修改后的翼型之间揭示了仿生结节增强的动量传递特性。