Hostname: page-component-cd9895bd7-gvvz8 Total loading time: 0 Render date: 2024-12-26T07:41:22.312Z Has data issue: false hasContentIssue false
  • English
  • Français

Evaluation of CFD methods for transport aircraft high lift systems

Published online by Cambridge University Press:  03 February 2016

R. Rudnik ,
P. Eliasson  and
J. Perraud
R. Rudnik
Affiliation:
DLR, German Aerospace Center, Institute of Aerodynamics and Flow Technologies, Braunschweig, Germany
P. Eliasson
Affiliation:
FOI, Swedish Defense Research Agency, Aeronautics Division, Stockholm, Sweden
J. Perraud
Affiliation:
ONERA, Office National d’Etudes et de Recherches Aerospatiales, CERT/DMAE, Toulouse, France
Get access Rights & Permissions [Opens in a new window]

Abstract

Major results and findings of the numerical work package of the European high lift programme EUROLIFT are outlined. The main objective of these studies is to validate and test numerical methods for the prediction of high lift flows for transport aircraft configurations. The activities comprise the assessment of current CFD methods for 3D flows, evaluation of means for code improvement, and transition prediction. All aspects are especially devoted to high lift flow problems. A general capability to predict maximum lift on a simplified wing/fuselage high lift configuration is demonstrated by a variety of different numerical approaches. In general, major shortcomings are the reliability and the accurate simulation of large separation areas and the turn-around time to compute 3D lift polars. Advanced turbulence modelling and numerical solver features, such as the preconditioning technique, show a potential to overcome these deficiencies. Promising results with respect to transition prediction were obtained on a swept high lift wing using a database method. The results obtained in the numerical activities represent major ingredients on the way to a consistent numerical approach for the simulation of transport aircraft high lift configurations including all maximum lift determining effects.

Type
Research Article
Information
The Aeronautical Journal , Volume 109 , Issue 1092 , February 2005 , pp. 53 - 64
Copyright
Copyright © Royal Aeronautical Society 2005 

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. Rumsey, L.R. and Ying, S.X.. Prediction of high lift: review of present CFD capability, Prog in Aerospace Sci, 2002, 38, pp 145–180.Google Scholar
2. Lindblad, I.A.A. and De Cock, K.M.J., CFD Prediction of maximum lift of a 2D high lift configuration, 1999, AIAA-99-3180.Google Scholar
3. Thibert, J.J.. The Garteur high lift research programme, AGARD-CP-515 High Lift System Aerodynamics, 1993, pp 16–1 – 16–21.Google Scholar
4. Thiede, P.. Eurolift — advanced high lift aerodynamics for transport aircraft, Air & Space Europe, 2001, 3, (3/4), pp 1–4.Google Scholar
5. Rudnik, R.. Towards CFD validation for 3D high lift flows — EUROLIFT, 2001, European Congress on Computational Methods in Applied Science and Engineering, ECCOMAS conference proceedings, IMA, ISBN 0 905 091 124 (CD-ROM), pp 1–20.Google Scholar
6. Schwarz, T.. Development of a wall treatment for Navier-Stokes computations using the overset-grid technique, 200, Paper No 45, Proceedings of the 26th European Rotorcraft Forum, 26-29 September 2000, The Hague, The Netherlands.Google Scholar
7. Edwards, J.R. and Chandra, S.. Comparison of eddy viscosity-transport turbulence models for three-dimensional shock separated flowfields, AIAA J, April 1996, 4.Google Scholar
8. Wallin, S. and Johansson, A.V.. An explicit algebraic Reynolds stress model for incompressible and compressible turbulent flows, J Fluid Mech, 2000, 403, pp 89–132.Google Scholar
9. Eliasson, P., CFD Improvements for high lift flows in the European project EUROLIFT, 2003, AIAA-2003-3795, Orlando, FL, USA.Google Scholar
10. Hansen, H. and Szabo, I.. Investigation of stall characteristics of an A3XX relevant airfoil up to high Reynolds numbers in the technology Program HAK 2, Notes on Numerical Fluid Mechanics, 1999, 72, Vieweg Braunschweig.Google Scholar
11. Rudnik, R.. Common European CFD-code validation for complex high lift configurations — the challenge of coming from observations to conclusions, 2002, DGLR Jahrestagung, Stuttgart, Germany, DGLR-Jahrbuch 2002, Bd III, JT 2002–015.Google Scholar
12. Choi, Y.H. and Merkle, C.L.. The application of preconditioning to viscous flows, J Computational Physics, 1993, 105, pp 207–223.Google Scholar
13. Weiss, J.M. and Smith, W.A.. Preconditioning applied to variable and constant density flows, AIAA J, 1995, 33, (11), pp 2050–2057.Google Scholar
14. Arnal, D.. Transition prediction in transonic flows, 1988, Zierep, and Oertel, (Eds), IUTAM Transsonicum III Symp, Göttingen.Google Scholar
15. Casalis, G. and Arnal, D., Database method — development and validation of the simplified method for pure crossflow instability at low speed 1996, ELFIN II Tech Rep N° 145.Google Scholar
16. Séraudie, A., Perraud, J. and Moens, F.. Transition measurement and analysis on a swept wing in high lift configuration, December 2003, AST, 7, (8), pp 569–576.Google Scholar
17. Pfenninger, W.. Flow phenomena at the leading edge of swept wings, Recent Dev in Boundary Layer Research, 1965, AGARDograph 97.Google Scholar
18. Smith, A.M.O. and Gamberoni, N.. Transition, pressure gradient and stability theory, 1956, Douglas Aircraft Co, Rept ES 26388, El Segundo, CA, USA.Google Scholar
19. Gregory, N., Stuart, J.T. and Walker, W.S.. On the stability of three dimensional boundary layer with application to the flow due to a rotating disc, Philosophical Transaction of the Royal Society of London, 1955, A 248, pp 155–199, London, UK.Google Scholar
20. Gaster, M.. A note on the relation between temporally increasing and spatially increasing disturbances in hydrodynamic stability, J Fluid Mechanics, 1962, 14, pp 222–224.Google Scholar
21. Beasley, J.A.. Calculation of the laminar boundary layer and prediction of transition on a sheared wing, 1976, RAE Farnborough Rep N° 3787.Google Scholar
22. Arnal, D. and Juillen, J.C.. Leading edge contamination and relami-narisation on a swept wing at incidence, 1989, Fourth Symposium on Numerical and Physical Aspects of Aerodynamics Flows, Calif State Univ.Google Scholar