The aim of this work is to describe an integrated simulation procedure based on the coupling of aeroelasticity, aerodynamics and aeroacoustics analysis, developed within AGUSTA in order to predict helicopter noise footprints in wind tunnel testing as in real flight conditions, under the assumption of stabilised manoeuvring conditions. Application of the simulation methodology can be helpful not only during analysis, in order to determine noise contour levels emitted in various flight manoeuvres (particularly those requested by certification needs), but also a priori as a design tool to orient design choices towards containing environmental impact of the helicopter. As a matter of fact most of recent works involving industries and research establishments extensively refer to interpolated data from experimental database, surely in order to maintain affordable calculation times free from those, usually heavy, of CFD methodologies, but primarily due to the fact that the various aeroacoustic tools developed lack exhaustive validation if extended to the whole flight envelope. Far less usual for these reasons are applications that determine noise contour levels as result of a complete loop that only makes use of simulation tools. This paper is intended to be a description of the simulation system general architecture and to describe the preliminary validation activity conducted on a wind tunnel model rotor.
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