On an unsteady aerodynamics model for pitching-oscillating body at high angle of attack

An improved state space representation for the unsteady aerodynamics with large angle of attack was presented. The first order differential equation proposed by Goman. was used to model the dynamics of flow separation and vortex burst, but unsteady effect of the rate of dynamic motion of the airframes was considered. The aerodynamic coefficients can express as an algebraic series in terms of input variables. Based on wind tunnel test data, the unknown parameters in the model can be identified by minimum mean square method and maximum likelihood method. Three examples of the unsteady aerodynamic model with large angle of attack were analyzed. It is shown that the performance of the present model is much better than one of Goman's original model.