Tiltwing aircraft represents a possible future evolution of conventional tiltrotors. Indeed, by making use of smaller rotors, a tiltwing is able to hover in helicopter mode, to achieve very high forward speed in cruise flight in aeroplane mode and to allow for horizontal taking off and landing. The partial tilting wing concept, introduced in 2000 in the ERICA tiltrotor design, made the tiltwing solution even more attractive. Although this promising configuration was widely studied, many aspects require further analysis. In the present work, the initial stage of the transition manoeuvre that allows a tiltwing aircraft employing the partial tilting wing solution to convert from helicopter to aeroplane mode is investigated. An extensive wind tunnel test campaign carried out in the Politecnico di Milano Large Wind Tunnel is described and the effects due to the aerodynamic interaction between wing and rotor are discussed. Aircraft performance are also discussed to assess the effectiveness of this aircraft design.

Wing-Rotor Aerodynamic Interference on a Tiltwing Aircraft in the First Part of Conversion Manoeuvre

DROANDI, GIOVANNI;GIBERTINI, GIUSEPPE;GRASSI, DONATO;CAMPANARDI, GABRIELE GIUSEPPE;
2016

Abstract

Tiltwing aircraft represents a possible future evolution of conventional tiltrotors. Indeed, by making use of smaller rotors, a tiltwing is able to hover in helicopter mode, to achieve very high forward speed in cruise flight in aeroplane mode and to allow for horizontal taking off and landing. The partial tilting wing concept, introduced in 2000 in the ERICA tiltrotor design, made the tiltwing solution even more attractive. Although this promising configuration was widely studied, many aspects require further analysis. In the present work, the initial stage of the transition manoeuvre that allows a tiltwing aircraft employing the partial tilting wing solution to convert from helicopter to aeroplane mode is investigated. An extensive wind tunnel test campaign carried out in the Politecnico di Milano Large Wind Tunnel is described and the effects due to the aerodynamic interaction between wing and rotor are discussed. Aircraft performance are also discussed to assess the effectiveness of this aircraft design.
42nd European Rotorcraft Forum (ERF 2016)
9781510839144
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Utilizza questo identificativo per citare o creare un link a questo documento: http://hdl.handle.net/11311/997843
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