Mechanism of single-mode panel flutter in low supersonic flow

Supersonic panel flutter can be of two possible types: single -mode flutter and coupled -mode flutter. Compared to coupled -mode flutter, the physical mechanism of single -mode flutter is less studied at present. In order to reveal the inducing mechanism of single -mode flutter, the present paper constructed a reduced -order fluid model by using the system identification and the Auto Regressive with eXogenous input (ARX) model. Coupling the reduced -order model (ROM) for unsteady aerodynamics in low supersonic flow with the structural equation, a highly efficient ROM -based aeroelastic model in state space is formulated, then the flutter boundaries are obtained and the stability of aeroelastic modes are investigated by the complex eigenvalue analysis. According to the physical meaning of relevant parameters in unsteady aerodynamic reduced order model ARX, it is found that the unsteady characteristic of the flow, specifically the history effects of the unsteady aerodynamic forces, plays a dominant role in causing the single -mode panel flutter at low supersonic speeds. It is also shown that the higher modes are indeed weakly unstable in the absence of any structural damping or a viscous boundary layer.