可变后掠机翼变形机理及气动特性研究

Research on Deformation Mechanism and Aerodynamic Characteristics of Variable Swept Wing

在飞行器的设计开发过程中,机翼后掠角的改变可以使飞行器在各个飞行阶段均保持较优的性能。本文提出一种局部旋转式变后掠机翼,并设计了相应的驱动机构。将此变后掠方案结合两种不同翼型分别构建三维模型后,基于FLUENT及SA湍流模型,对两模型分别进行了外部绕流流场的数值模拟,分析机翼在不同攻角及飞行马赫数下的气动特性差异。分析结果表明,通过改变机翼的后掠角改变可以显著改变机翼升力系数、阻力系数及升阻比,提高飞行器对不同飞行环境的适应能力。

In the process of design and development of aircraft,the change of wing sweep angle can make the aircraft maintain better performance in each flight stage.In this paper,a local rotary variable swept wing is proposed and the corresponding driving mechanism is designed.After the three-dimensional model is constructed by combining the two different airfoils,the flow field around the two models is simulated based on fluent and SA turbulence model respectively,and the aerodynamic characteristics of the wing under different attack angles and Mach numbers are analyzed.The results show that the lift coefficient,drag coefficient and lift resistance ratio of the wing can be significantly changed by changing the sweep angle of the wing,and the adaptability of the aircraft to different flight environments can be improved.