Transonic flutter characteristics of aircraft T-tail

Due to the features of T-tail in structural and aerodynamic configurations, the effects of in-plane motion and steady aerodynamics of horizontal plane, as well as the inaccuracy in the calculation of transonic compressibility and unsteady transonic flow, the transonic flutter calculation of aircraft T-tail is much more difficult. In the analysis of transonic flutter of aircraft T-tail priority should be given first to transonic wind tunnel test and then to calculation. For a certain type of aircraft T-tail, the transonic flutter characteristics were simulated by using the method of ZTAIC in software ZAERO and the effects of Mach number, flow air density and stabilizer attack angle were investigated. The well known 'transonic dip' phenomenon and compressibility characteristic of the T-tail model were captured based on the present method in transonic wind tunnel tests and at the same time calculated by using the method of lift curve slope compressibility correction. The results of these two methods are in good agreement.