Successive smoothing algorithm for constructing the semiempirical model developed at ONERA to predict unsteady aerodynamic forces

摘要

Unsteady aerodynamic methods adopted for the study of aeroelasticity in helicopters are considered with focus on the development of a semiempirical model of unsteady aerodynamic forces acting on an oscillating profile at high incidence. The successive smoothing algorithm described leads to the model's coefficients in a very satisfactory manner.