Abstract: A new mathematical model of unsteady aerodynamics of airplane at high angles of attack is developed, with employment of a one order differential equation to describe the aerodynamic increment caused by nonlinear unsteady effects. The linearized form of the model and the expression for dynamic derivatives are researched. The identification problem of the parameters in the model is discussed. At last, the accuracy of the aerodynamic mathematical model and the effectiveness of the parameter identification method presented in the paper are illustrated in the calculation example.