By approaches of vortex rotor blade theory and blade element theory a modified tail rotor that has irregular location of blades in the planes of rotation nearby helicopter tail fin aerodynamic performances are researched on the mode of the axial flowing around of a combination. It is set that helicopter tail fin negatively influencing on a modified tail rotor nearby helicopter tail fin combination by tendency of total output-input ratio diminishing, By comparison of aerodynamic loading change characters between tail rotors that have three blades and four blades in different planes of rotation it is set that nearby helicopter tail fin for the complete turn of the modified tail rotor observed not three, but two characteristic splashes of aerodynamic loading.
Helicopter, tail rotor, tail fin, interference, aerodynamic performances
"Doslidzhennia aerodynamichnykh kharakterystyk modyfikovanoho rulovoho hvynta v prysutnosti kilia vertolota na rezhymi osovoho obtikannia" ,
Scientific Works of Kharkiv National Air Force University,