Abstract:Transition phenomenon has an impact on transonic flow filed and aerodynamic force, but most of the current researches about flutter use fully turbulent hypothesis, which have no consideration about transition phenomenon. Therefore, using unsteady Reynold Averaged Navier-Stockes (RANS) equation and transition model, as well as structure dynamic equation to establish the time domain aeroelastic analysis method. The solution in time domain is fourth order implicit Adams linear multi-step method which is based on prediction-correction method. The numerical simulations were used to analyze the transonic flutter boundary of Isogai Case A Model which was based on fully turbulent hypothesis and transition model respectively. These simulations were also made to analyze the influence mechanism of transition to flutter characters from the point of view about aerodynamic work. The results show that transition phenomenon make the transonic dip deeper and wider than fully turbulent flow. Flutter speed in the deepest position of transonic dip has decreased by 41.6%. Therefore, when flutter characters of wing which has transition on its surface is analyzed, transition model must be added into fluid equations in order to analyze flutter boundary correctly.
李国俊 1,白俊强 1,刘南 1,徐家宽 1,乔磊 1. 基于转捩模型的二维翼型跨音速颤振边界预测[J]. 振动与冲击, 2017, 36(22): 205-211.
Li Guo-jun 1 Bai Jun-qiang 1 Liu Nan 1 Xu Jia-kuan 1 Qiao Lei 1. Flutter Boundary Prediction of a Two Dimensional Airfoil in Transonic Flight Regime with the Transition Model. JOURNAL OF VIBRATION AND SHOCK, 2017, 36(22): 205-211.
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