Abstract
In the time domain aerodynamics calculation, a new approach for flow field boundary controlling is suggested in the present study, in which the wing was forced to oscillate harmonically under small amplitude. The transonic aerodynamic force was computed by solving unsteady Euler equations, and then modal aerodynamic force was calculated using modal matrix. The least square method is used to fit the modal aerodynamic force coefficient time history. From the physical meaning of aerodynamic influence coefficient ( AIC ) matrix, the formulation of AIC matrix are derived according to time domain solution of modal aerodynamic force. Based on the transonic AIC matrix, wing transonic flutter characteristics can be obtained by frequency domain flutter solution. The transonic flutter charac-teristics of AGARD 445.6 wing are studied and the flutter boundary under different Mach numbers was presented. The results obtained by the present method are in good agreement with those obtained by experimental data of literatures.
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