Hostname: page-component-848d4c4894-pftt2 Total loading time: 0 Render date: 2024-06-07T21:19:36.222Z Has data issue: false hasContentIssue false
  • English
  • Français

Numerical simulation of wing vortex generators – methodologies and validation

Published online by Cambridge University Press:  20 April 2016

M. Zastawny
M. Zastawny*
Affiliation:
Aircraft Research Association, Bedford, UK
*
mzastawny@ara.co.uk
Get access Rights & Permissions [Opens in a new window]

Abstract

This paper presents the results of a study of different Vortex Generator (VG) modelling approaches that have been performed in order to develop a better understanding of the current Computational Fluid Dynamics (CFD) capability to simulate transonic flows where wing-mounted VGs are present.

The practicality of using CFD methods commonly employed in the aerospace industry to predict the influence of VGs on wing performance is studied. It is hoped that presenting the experience gained will be of value to aerodynamicists working on similar problems in industry. An approach, using fully resolved, conformal mesh around the VGs, has been investigated through studying Reynolds-Averaged Navier Stokes (RANS) simulations with two alternate turbulence models, the Spalart-Allmaras (SA) model and the Speziale-Sarkar-Gatski (SSG) Reynolds Stress Model. An initial assessment of two alternative VG modelling techniques, use of the Chimera overset meshing and a reduced-order VG model has also been performed. In addition, an investigation of the impact of the wing deformation under aerodynamic loading was conducted. The results obtained were compared with the wind-tunnel measurements acquired in the Aircraft Research Association Transonic Wind Tunnel, using the N47-05 half model with installed VGs.

It was observed that the VGs significantly modify the flow behaviour at sufficiently high incidence, which leads to higher lift coefficient values. While the SA turbulence model was unable to capture the complicated nature of the flow when VGs were present, SSG simulations yielded promising results.

Each of the VG modelling approaches has shown some strengths and weaknesses. Further study on the subject is suggested in order to develop best practices that can be applied for solutions of industrial-scale problems.

Keywords

Vortex generatorsReynolds-stress modelwind tunneldata comparison
Type
Research Article
Information
The Aeronautical Journal , Volume 120 , Issue 1226 , April 2016 , pp. 627 - 650
Copyright
Copyright © Royal Aeronautical Society 2016 

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

REFERENCES

1. Rolston, S. High Reynolds number tools and techniques for civil aircraft design. AIAA Paper 2001-2411, June 2001.Google Scholar
2. ESDU. Vortex generators for control of shock-induced separation. Part 1: introduction and aerodynamics; ESDU transonic Data Memor. No. 93024, December 1993 (with Amendment A, February 1995).Google Scholar
3. Booker, C.D., Zhang, X. and Chernyshenko, S.I. Large-scale vortex generation modelling, J Fluids Engineering, 2011, 133, (12), pp 121201.CrossRefGoogle Scholar
4. Joubert, G., Le Pape, A. and Huberson, S. Numerical study of flow separation control over a OA209 airfoil using deployable vortex generator, 49th AIAA Aerospace Sciences Meeting, 2011, Orlando, Florida, US.Google Scholar
5. Abbas, A., De Vicente, J. and Valero, E. Aerodynamic technologies to improve aircraft performance, Aerospace Science and Technology, 2013, 28, (1), pp 100–132.CrossRefGoogle Scholar
6. Hahn, M. Transonic flow over the N47-05 half-model: Part I – Analysis of numerical and experimental clean-wing data, ARA Contractor Report RAH00402/1, March 2014.Google Scholar
7. Martineau, D.G. et al. Anisotropic hybrid mesh generation for industrial RANS applications, AIAA Paper 2006-0534, January 2006.Google Scholar
8. Schwamborn, D., Gerhold, T. and Heinrich, R. The DLR TAU-code: Recent applications in research and industry. Proceedings of the European Conference on Computational Fluid Dynamics, ECCOMAS CFD 2006, 5-8 September 2006, Delft University of Technology, Egmond aan Zee, The Netherlands.Google Scholar
9. Spalart, P.R. and Allmaras, S.R. A one-equation turbulence model for aerodynamic flows, La Recherché Aerospatiale, 1994, 1, pp 5–21.Google Scholar
10. Cécora, R.-D., Radespiel, R., Eisfeld, B. and Probst, A. Differential Reynolds-stress modeling for aeronautics, AIAA J, 2015, 53, (3), pp 739–755.Google Scholar
11. Zastawny, M. DRSM results for a flat plate boundary layer using TAU, ARA Contractor Report AAH00903/2, December 2013.Google Scholar
12. Zastawny, M. Transonic flow over the N47-05 half-model: Part II – Vortex generator study, ARA Contractor Report RAH00402/2, March 2014.Google Scholar
13. Bender, E.E. et al. Vortex generator modelling for Navier-Stokes codes, 3rd Joint ASME/JSME Fluid engineering Conference, Paper No. FEDSM99-6919, July 1999, San Francisco, California, US.Google Scholar
14. Törnblom, O. and Johansson, A.V. A Reynolds stress closure description of separation control with vortex generators in a plane asymmetric diffuser, Physics of Fluids, 2007, 19, (11), pp 115108.Google Scholar