Presented a method of the operational calculation nonlinear aerodynamic characteristics of single-rotor helicopter tail rotor. The method is based on the using of elements of the vortex theory blade propeller with aerodynamic characteristics of profile blade. The method allows to reliably determine the nonlinear aerodynamic characteristics of the tail rotor with minimal requirements to computer resources.
tail rotor, nonlinear aerodynamic characteristics, the polar, the angle of attack, the coefficient of resistance, the lift coefficient
"Metod operatyvnoho rascheta aэrodynamycheskykh kharakterystyk rulevoho vynta vertoleta dlia zadach ymytatsyy dynamyky poleta vertoleta na trenazherakh" ,
Science and Technology of the Air Force of Ukraine,