The Effect of Nonlinear Aerodynamic Characteristics on the Dynamic Response to a Sudden Change in Angle of Attack

Abstract

The effect of nonlinear pitching moment and lift variations with angle of attack on the dynamic response to a sudden change in angle of attack is considered. An approximate solution to the nonlinear equation of motion is developed. Several numerical examples are considered, and the results of the approximate solution are compared with the accurate results of numerical integration, as well as the classical linearized solution. The effect of a nonlinear moment curve on the determination of stability derivatives from flight-test data is discussed in the light of these examples.