A nonlinear blade vortex propeller theory and its applications to estimate aerodynamic characteristics for helicopter main rotor and anti-torque rotor

Аuthors

Ignatkin Y. M.^1*, Makeev P. V.^**, Grevtsov B. S.^1***, Shomov A. I.^2****

1. Moscow Aviation Institute (National Research University), 4, Volokolamskoe shosse, Moscow, А-80, GSP-3, 125993, Russia
2. National Helicopter Center Mil & Kamov, 26/1, Garshina str., Tomilino, Moscow region, 140070, Russia

*e-mail: k102@mai.ru; ignatkinym@mai.ru
**e-mail: vaultcity13@gmail.com
***e-mail: grevcov_tut@mail.ru
****e-mail: shomov_aleksandr@mail.ru; a.shomov@nhc.aero

Abstract

A technique is presented to analyze aerodynamic characteristics of helicopter rotors basing on nonlinear blade vortex theory taking into account vortex diffusion. Basic features of the suggested model are discussed as well as possible applications of the model. Some investigation results are demonstrated for rotors at various operation modes.

Keywords:

helicopter main rotor, vortex model, diffusing vortex, aerodynamic characteristics, vortex wake, blade layout