A Research on Transonic Flutter Characteristic of Aircraft T-Tail
ANG Fei1 YANG Zhichun2
1.Stress Department, Shanghai Aircraft Design And Research Institute of COMAC, Shanghai, 200232, China2. School of Aeronautics, Northwestern Polytechnical University, Xi’an, 710072
Abstract：The flutter calculation method to conventional aircraft tail wing can not be applied directly to T-tail flutter analysis due to its features in structural and aerodynamic configurations, and the effects of in-plane motion and steady aerodynamics of horizontal plane should be considered in T-tail flutter calculation. Because transonic compressibility and unsteady Transonic flow of T-tail is difficult, the transonic flutter of aircraft T-Tail calculation is more difficult and inaccurate. Transonic flutter of aircraft T-Tail calculation Method should give priority to transonic wind tunnel test and give secondary to calculation. For aircraft T-tail, the transonic flutter characteristic is also simulated using ZAERO soft ZTAIC and the effect of the Mach number, flow air density and stabilizer attack angle is investigated. The well known ‘Transonic Dip’ phenomenon and compressibility Characteristic has been captured for T-tail model using the present method in transonic wind tunnel and lift curve slope compressibility correct method. The results of the lift curve slope compressibility correct method agreed well with the transonic wind tunnel as T-tail model result.
杨飞;杨智春. 飞机T型尾翼跨音速颤振特性研究[J]. , 2013, 32(10): 50-54.
ANG Fei YANG Zhichun. A Research on Transonic Flutter Characteristic of Aircraft T-Tail. , 2013, 32(10): 50-54.
2013, Vol. 32 
