Numerical study of helicopter blade-vortex mechanism of interaction using the potential flow theory

    Authors

    P. X. C. Domenge;M. Ilie

    Comments

    Authors: contact us about adding a copy of your work at STARS@ucf.edu

    Abbreviated Journal Title

    Appl. Math. Model.

    Keywords

    Helicopter blade-vortex interaction; Potential flow; Vortex Panel Method; Engineering, Multidisciplinary; Mathematics, Interdisciplinary; Applications; Mechanics

    Abstract

    The blade-vortex interaction (BVI) phenomenon plays a key role in the rotorcraft aerodynamics. Numerical investigations of BVI using classical CFD approaches are computationally expensive. In the present research we propose a numerical approach, based on the potential flow theory, for the numerical investigation of helicopter blade-vortex mechanism of interaction. This approach overcomes the computational expenses posed by the CFD techniques. The influence of vertical miss distance, angle of attack, airfoil camber, and vortex strength on the helicopter blade-vortex mechanism of interaction is subject of investigation. The study reveals that the magnitude of the aerodynamic coefficients decreases with the increase of vertical miss distance and angle of attack, and the decrease of vortex strength and core size. (C) 2011 Elsevier Inc. All rights reserved.

    Journal Title

    Applied Mathematical Modelling

    Volume

    36

    Issue/Number

    7

    Publication Date

    1-1-2012

    Document Type

    Article

    Language

    English

    First Page

    2841

    Last Page

    2857

    WOS Identifier

    WOS:000303228700002

    ISSN

    0307-904X

    Share

    COinS