仿生非光滑表面机翼的气动性能数值模拟

Numerical Simulation of Aerodynamic Performance of Wing with Bionic Non-smooth Surface

根据仿生微小非光滑表面具有减黏降阻特性的特点,对NACA 2412翼型进行仿生改造,提出2种仿生机翼,即分别在机翼的上下表面布置相同数目、相同尺寸的非光滑矩形状条纹结构。基于Fluent软件,应用雷诺平均法分析原机翼模型和改造后2种仿生非光滑机翼模型在不同攻角下的气动性能。结果表明,在机翼下表面添加条纹结构改善机翼的气动性能,机翼上表面添加条纹结构破坏机翼的气动性能。

bAccording to the resistance reduction characteristic of bionic non-smooth surface, two kinds of bionic models were proposed to modify the NACA 2412 airfoil. Non-smooth rectangular stripes with the same quantity and size were arranged on the upper and lower surface of the wing, respectively.With the software Fluent, the aerodynamic performances of the original wing and two kinds of bionic non-smooth wing under different attack angles were analyzed by Renault average method. The results show that attaching stripe structures to the bottom surface of the wing improves the aerodynamic performance of the wing, while attaching stripe structures to the top surface harms the aerodynamic performance of the wing.