A method for calculating parallel blade vortex interaction (BVI) has been developed. The technique is based on the application of a three-dimensional aeroacoustic boundary element formulation using Analytical/Numerical Matching in conjunction with a recently developed viscous core trailing vortex roll-up model. Computational parameters were chosen to correspond with an experimental investigation conducted at NASA Ames Research Center modeling parallel BVI between a model rotor and an independently generated trailing vortex. Calculations include rotor blade chordwise pressure distributions, blade surface pressure time histories, and both near- and far-field radiated acoustic pressure time histories. Comparisons with experimental data demonstrate the feasibility of applying linear theory to the study of BVI.
Unsteady compressible boundary element calculations of parallel blade-vortex interaction
Instationäre kompressible Rand-Element-Berechnungen von parallelen Rotorblatt-Wirbel-Interaktionen
Journal of the American Helicopter Society ; 44 , 4 ; 302-311
1999
10 Seiten, 13 Bilder, 48 Quellen
Article (Journal)
English
Hubschrauber , Rotor (Drehflügel) , Wirbelströmung , Wechselwirkung , Berechnungsverfahren , Rand-Elemente-Methode , Simulationsmodell , Schallemission , dreidimensionale Strömung , analytische Untersuchung , Vergleichsmessung , Versuchsmodell , Tragflügel , Druckverteilung , Zeitverhalten , Schalldruck , Aeroakustik
Unsteady Compressible Boundary Element Calculations of Parallel Blade-Vortex Interaction
Online Contents | 1999
|Unsteady Compressible Boundary Element Calculations of Parallel Blade-Vortex Interaction
British Library Conference Proceedings | 1998
|Parallel blade-vortex interaction
Tema Archive | 1998
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