近日，北京航空航天大学的宋晨及其研究团队取得一项新进展。经过不懈努力，他们对具有开裂阻力方向舵翼型的跨声速颤振特性进行了数值研究。相关研究成果已于2024年11月12日在国际知名学术期刊《理论与应用力学快报》上发表。

本文通过一系列颤振模拟，研究了开裂式阻力方向舵（SDR）对刚性NACA 64A010翼型跨声速颤振特性的影响。研究人员将一个处理两自由度俯仰-沉浮气动弹性振荡的结构动力学模型，与非定常雷诺平均纳维-斯托克斯方程相结合，以进行颤振模拟。同时，本文通过气动功和相关的激波位置，解释了SDR对颤振边界的影响机制。

结果表明，SDR使激波向下游移动延缓，且随着开裂角度的增加，达到冻结区对应的马赫数也随之增加。因此，气动力矩系数振幅的峰值和相位的急剧上升过程，出现在更高的马赫数下，这导致了跨声速陡降的延迟。

此外，在没有SDR的翼型出现跨声速陡降之前，由于激波向下游移动的速度减慢，带有SDR的翼型的气动力矩相位缓慢减小。这导致在没有SDR的翼型出现跨声速陡降之前，使用SDR时颤振速度增加。同时，本文还研究了不对称开裂角度对跨声速颤振特性的影响。在没有SDR的翼型出现跨声速陡降之前，颤振特性主要由较小的开裂角度决定。

附：英文原文

Title: Numerical investigation on transonic flutter characteristics of an airfoil with split drag rudder

Author: Yongchang Li, Yuting Dai, Chen Song, Chao Yang, Guangjing Huang

Issue&Volume: 2024-11-12

Abstract: In this paper, a series of flutter simulations are carried out to investigate the effects of split drag rudder (SDR) on the transonic flutter characteristic of rigid NACA 64A010. A structural dynamic model addressing two-degree-of-freedom pitch-plunge aeroelastic oscillations was coupled with the unsteady Reynolds-averaged Navier-Stokes equations to perform flutter simulation. Meanwhile, the influence mechanism of SDR on flutter boundary is explained through aerodynamic work and the correlated shock wave location. The results show that the SDR delays the shock wave shifting downstream, and the Mach number corresponding to reaching freeze region increases as the split angle increases. Therefore, the peak value of aerodynamic moment coefficient amplitude and the sharp ascent process of phase occurs at higher Mach number, which leads to the delay in the occurrence of the transonic dip. Besides, before the transonic dip of airfoil without SDR occurs, the aerodynamic moment phase of airfoil with the SDR decreases slowly due to the decrease in the speed of shock wave moving downstream. This results in an increased flutter speed when employing the SDR before the transonic dip of airfoil without SDR occurs. Meanwhile, the effects of asymmetric split angles on the transonic flutter characteristics are also investigated. Before the transonic dip of airfoil without SDR occurs, the flutter characteristic is dominated by the smaller split angle.

DOI: 10.1016/j.taml.2024.100554

Source: http://taml.cstam.org.cn/article/doi/10.1016/j.taml.2024.100554pageType=en