Helicopter rotor in a propeller slipstream: Aerodynamic and rotor blade flapping responses

•The submitted article is based on the first analytical solution of a propeller's slipstream impingement on a helicopter rotorsw.•The rotor controls required to compensate for the disturbances are given.•For the first time the rotor blade flapping response due to the propeller disturbance is computed and discussed. During helicopter air-to-air refueling the helicopter's rotor can engage the tanker aircraft's wing and flap end tip vortices and the slipstream of its propellers. The tip vortices represent a swirl around an axis that is essentially parallel to the rotor longitudinal axis. The slipstream of the propellers includes a strong air jet downstream that can cover a significant amount of the helicopter's main rotor. This phenomenon was recently treated analytically for a rigid rotor by means of blade-element momentum theory and the rotor control angles required to reject the disturbance were computed. In this article, the rotor blade flapping is introduced as degree of freedom. It is shown that the rotor coning is affected by the slipstream position with respect to the rotor hub. Without retrim, the largest amount of coning and cyclic flapping occurs for slipstream positions on the retreating side of the rotor.