AEROMECHANICS MODELLING OF TILTROTOR AIRCRAFT

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Abstract

A numerical investigation into the effects of aerodynamic interaction modelling for tiltrotor aircraft is undertaken. The study compares a baseline case, with no interaction accounted for, with those that include the download on the wing and the rotor and wing wakes at the empennage against literature models. The results are obtained using a reduced-order blade element/strip theory framework and simulates the entire conversion corridor. The results are compared for trimmed pitch attitude and control stick position, showing the most important interaction to account for is the wing downwash. This interaction increases trimmed pitch attitude in low-speed helicopter and early conversion mode, decreases the forward stick towards aeroplane mode, and affects the flight speeds boundaries through the conversion corridor.
Original languageEnglish
Title of host publicationEuropean Rotorcraft Forum
Publication statusAccepted/In press - 1 Aug 2019
Event45th European Rotorcraft Forum - Warsaw, Poland
Duration: 17 Sept 201920 Sept 2019

Conference

Conference45th European Rotorcraft Forum
Country/TerritoryPoland
CityWarsaw
Period17/09/1920/09/19

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