A mathematical model for rapid calculation of nonlinear aerodynamic characteristics of the helicopter single-rotor design for modeling dynamics of flight on the helicopter simulators is developed. The model takes into account the nonlinear effects due to the influence of compressibility and viscosity of the medium, stalling and end of the overflowing on propeller blades, and allows you to simulate the boundary and critical modes of helicopter flight, except when "vortex ring". Examples of calculations of the aerodynamic characteristics of the helicopter, the results of which are in good agreement with the experimental data are presented.
nonlinear aerodynamic characteristics of the helicopter, inductive speed, main rotor, rotor angle of attack, the longitudinal balancing
"Matematycheskaia model nelyneinoi aэrodynamyky vertoleta odnovyntovoi skhemы dlia zadach modelyrovanyia dynamyky poleta na vertoletnыkh trenazherakh" [Mathematical models of nonlinear aerodynamics helicopter single-rotor scheme for the problem of modeling dynamics of flight on the helicopter simulators],
Information Processing Systems,