Some results, relevant to rotorcraft noise generation process at high advance ratio, are presented in this paper from schlieren flow visualization and acoustic tests of a model tail rotor. The measured in-plane noise trends are consistent with the growth of the tip supersonic region seen in the schlieren visuals. Schlieren flow visuals reveal a propagating pressure wave in the second quadrant. Simultaneously measured acoustic data and the results of two-dimensional transonic Blade-Vortex Interaction analysis code ATRAN-2 indicate that this pressure wave is attributable to BVI activity in the first quadrant. This paper establishes that the transonic Blade-Vortex Interactions contribute to noise at high advance ratio level flight conditions.
Aeroacoustic flowfield and acoustics of a model helicopter tail rotor at high advance ratio
AHS Annual Forum ; 1989 ; Boston, MA, United States
01.01.1989
Aufsatz (Konferenz)
Keine Angabe
Englisch
Helicopter rotor aerodynamic and aeroacoustic environments
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