Numerical study of helicopter blade-vortex mechanism of interaction using the potential flow theory
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
ISSN
0307-904X
Recommended Citation
"Numerical study of helicopter blade-vortex mechanism of interaction using the potential flow theory" (2012). Faculty Bibliography 2010s. 2494.
https://stars.library.ucf.edu/facultybib2010/2494
Accessibility Statement
This item was created or digitized prior to April 24, 2027, or is a reproduction of legacy media created before that date. It is preserved in its original, unmodified state specifically for research, reference, or historical recordkeeping. In accordance with the ADA Title II Final Rule, the University Libraries provides accessible versions of archival materials upon request. To request an accommodation for this item, please submit an accessibility request form.
Comments
Authors: contact us about adding a copy of your work at [email protected]