These parameter uncertainties in the aerodynamic model may lead to conservative or optimistic prediction of stall flutter [3,4].
Then the stochastic polynomial chaos expansion method for stall flutter will be investigated.
What is more, in most of stall flutter application cases, such as wind tunnel state, the Mach number is lower than 0.3.
Then both unsteady aerodynamic and structure uncertainty were taken into consideration to investigate the dynamic stall flutter at low Mach number.
Since stall flutter is largely affected by dynamic stall and these parameters are related to dynamic stall, it is very important to get the relationship between these parameters and the force and moment.
The nonintrusive polynomial chaos method can be applied to aeroelastic limit cycle oscillations and dynamic stall flutter analysis with uncertainty.