Hostname: page-component-848d4c4894-pftt2 Total loading time: 0 Render date: 2024-05-13T05:55:35.838Z Has data issue: false hasContentIssue false
  • English
  • Français

Parametric studies of aerofoil-vortex interaction; a numerical approach using LES

Published online by Cambridge University Press:  27 January 2016

M. Ilie ,
F. Nitzsche  and
E. Matida
M. Ilie*
Affiliation:
University of Central Florida, Orlando, Florida, USA
F. Nitzsche
Affiliation:
Carleton University, Ottawa, Canada
E. Matida
Affiliation:
Carleton University, Ottawa, Canada
*
marcel.Ilie@ucf.edu
Get access Rights & Permissions [Opens in a new window]

Abstract

The influence of angle-of-attack and vortex-aerofoil vertical miss-distance on the aerofoil-vortex mechanism of interaction is investigated numerically using the large-eddy simulation approach. The study concerns the aerofoil-vortex interaction (AVI) phenomena encountered in the rotorcraft aerodynamics. The studies are performed for a Reynolds number of 1·3 × 106 based on the chord (c = 0·2m) of the aerofoil and free-stream velocity U = 100ms−1. The studies are conducted for three different angles-of-attack (α = 0°, and α = 5°, α = 10°) and vertical miss-distances (h = 0·0m, h = −0·01, h = −0·02m) respectively. The present study shows that the magnitude of lift coefficient and flow separation, at the instant of interaction, decay with the increase of angle-of-attack and vertical miss-distance.

Type
Research Article
Information
The Aeronautical Journal , Volume 115 , Issue 1173 , November 2011 , pp. 703 - 711
Copyright
Copyright © Royal Aeronautical Society 2011 

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

1. Horner, M.B. Saliveros, E. Kokkalis, A. and MCD. Galbraith, R.A. Results from a set of low speed blade-vortex interaction experiments, Experiments in Fluids, 1993, 14, pp 341–352.Google Scholar
2. Straus, J., Renzoni, P. and Mayle, R.E. Airfoil Pressure Measurements During a Blade Vortex Interaction and a Comparison with Theory, AIAA J, 1990, 28, (2), pp 222–228.Google Scholar
3. Renzoni, P. and Mayle, R.E. Incremental force and moment coefficients for a parallel blade-vortex Interaction, AIAA J, 1991, 29, (1), pp 6–13.Google Scholar
4. Abelló, J.C. and George, A.R. Rotorcraft BVI noise reduction by attitude modification. In: Paper presented at the 5th AIAA/CEAS aeroacoustics conference, Bellevue, Washington, USA, 10–12 May 1999.Google Scholar
5. Abello, J. and George, A. Wake displacement study of attitude and flight parameter modifications to reduce rotorcraft blade–vortex interaction (BVI) noise. In: Ninth AIAA/CEAS aeroacoustics conference, Hilton Head, SC; 12–14 May 2003.Google Scholar
6. Opoku, D.G., Triantos, D.G., Nitzsche, F. and Voutsinas, S.G. Rotorcraft Aerodynamic and Aeroacoustic Modelling Using Vortex Particle Methods. ICAS Paper No. 2002-299, 2002.Google Scholar
7. Wong, A., Nitzsche, F. and Khalid, M. Formulation of Reduced-Order Models for Blade-Vortex Interactions Using Modified Volterra Kernels, Paper No. 7, Proceedings: 30th European Rotorcraft Forum, 14-16 September 2004, Marseilles, France.Google Scholar
8. Nagarajan, S. and Lele, S. Prediction of Sound Generated by a Pitching Airfoil: A comparison of RANS and LES, 12th AIAA/CEAS Aeroacoustics Conference, 8-10 May 2006, Cambridge, MA, USA.Google Scholar
9. Lardeau, S. and Leschziner, M.A. Unsteady Reynolds-averaged Navier-Stokes computations of transitional wake/blade Interaction, AIAA, 2004, 42, (8), pp 1559–1571.Google Scholar
10. Felten, F. and Lund, T. Numerical Simulation of parallel Airfoil/Vortex Interaction Using a Zonal Hybrid RANS/LES Method, AIAA2005-5127Google Scholar
11. Smagorrinsky, J.S. General circulation experiments with the primitive equation, Monthly Weather Rev, 1963, 91, pp 99–164.Google Scholar
12. Lilly, D.K. On the application on the eddy viscosity concept in the inertial sub-range of turbulence, 1996, NCAR Manuscript, pp 195–200.Google Scholar
13. Germano, M., Piomelli, U., Moin, P. and Cabot, W.H. A dynamic subgrid-scale eddy viscosity model, Phys Fluids A, 1991, 3, (7), pp 1760–1765.Google Scholar
14. Menter, F.R. Two-equation eddy – viscosity turbulence models for engineering applications, 1994, AIAA J, 32, (8).Google Scholar
15. Bossel, H.H. Vortex computation by the method of weighted residuals using exponentials, J Computational Physics, 1970, 5, pp 359–382.Google Scholar
16. Leishman, J.G. Principles of Helicopter Aerodynamics, Cambridge University Press, Cambridge, UK, 2006 Google Scholar
17. Ilie, M. Numerical study of helicopter blade–vortex mechanism of interaction using large-eddy simulation, Computers and Structures, 2009, 87, pp 758–768.Google Scholar
18. Ilie, M. Icing Effect on the Aeroacoustics of Helicopter Blade-Vortex Interaction: A Numerical Study Using Large-Eddy Simulation, AIAA-2010-3855, 2010 Google Scholar
19. Ilie, M. Active Flow Control Technique for the Reduction of Helicopter BVI Noise; a Numerical Study Using Large-Eddy Simulation AIAA-2010-3871, 201.Google Scholar