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作 者:Yongchang Li Yuting Dai Chen Song Chao Yang Guangjing Huang
机构地区:[1]School of Aeronautic Science and Engineering,Beihang University,Beijing 100191,China [2]Tianmushan Laboratory Xixi Octagon City,Yuhang District,Hangzhou 310023,China [3]Hangzhou International Innovation Institute,Beihang University,Hangzhou 311115,China
出 处:《Theoretical & Applied Mechanics Letters》2025年第1期87-97,共11页力学快报(英文版)
摘 要: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.
关 键 词:Transonic flutter Energy map Shock wave Split drag rudder
分 类 号:V211.3[航空宇航科学与技术—航空宇航推进理论与工程]
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