Hostname: page-component-cd9895bd7-mkpzs Total loading time: 0 Render date: 2024-12-22T11:48:26.764Z Has data issue: false hasContentIssue false

Investigation of the three-dimensional flow over a 40° swept wing

Published online by Cambridge University Press:  27 January 2016

S. Zhang
Affiliation:
School of Mechanical, Aerospace and Civil Engineering, University of Manchester, Manchester, UK
A. J. Jaworski
Affiliation:
School of Mechanical, Aerospace and Civil Engineering, University of Manchester, Manchester, UK
J. T. Turner*
Affiliation:
School of Mechanical, Aerospace and Civil Engineering, University of Manchester, Manchester, UK
N. J. Wood
Affiliation:
Formerly School of Engineering, Victoria University of Manchester now Airbus UK, Bristol, UK

Abstract

Three-component laser Doppler anemometry (LDA) has been used to measure the complex flow distributions over the suction surface of a symmetrical 40°swept wing model at an angle of incidence of 9° and for the relatively low Reynolds number (based on the root chord) of 2·1 × 105. Emphasis was placed on the separation and reattachment of the boundary-layer flow, and the formation of vortical structures.

The experimental programme now described utilised a large wind tunnel and several advanced measurement techniques to produce an unusually detailed collection of results. Thus, data are presented here for the behaviour of the three-dimensional boundary layer developing on the suction surface at positions from 30% to 90% semi-span. These results show the spatial variations of the time-averaged mean and fluctuating velocity components in three orthogonal directions, including the distributions of the normal and shear stress levels. Further analysis has enabled the time-averaged vortical structures to be identified and compared with the results of surface flow visualisation.

Flow over a swept wing poses many challenges for the computational modeller. The underlying aim, here, therefore, was to produce a data archive for the validation of computer predictions. As will be shown, some of the experimental results have already been used in this way and the data base is available for use by other workers.

Type
Research Article
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. Riley, A.J. and Lawson, M.V. Development of a three-dimensional free shear layer, J Fluid Mechanics, 1998, 369, pp 4989.Google Scholar
2. Gursul, I. Review of unsteady vortex flows over slender delta wings, J Aircr, 2005, 42, (2), pp 299319.Google Scholar
3. Gursul, I., Gordnierb, R. and Visbal, M. Unsteady aerodynamics of nonslender delta wings, Progress in Aerospace Sciences, 2005, 41, pp 515557.Google Scholar
4. Ol, M.V. and Gharib, M. Leading-edge vortex structure of non-slender delta wings at low Reynolds number, AIAA J, 2003, 41, (1), pp 1626.Google Scholar
5. Yaniktepe, B. and Rockwell, D. Flow structure on a delta wing of low sweep angle, AIAA J, 2004, 42, (3), pp 513-23.Google Scholar
6. Rockwell, D. Three-dimensional flow structure on delta wings at high angle-of-attack: experimental concepts and issues. AIAA 93-0050, 31st AIAA Aerospace Sciences Meeting & Exhibit, 11-14 January 1993, Reno, NV, USA.Google Scholar
7. Yavuz, M.M., Elkhoury, M. and Rockwell, D. Near-surface topology and flow structure on a delta wing, AIAA J, 2004, 42, (2), pp 332-40.Google Scholar
8. Li, N. and Leschziner, M.A. Large-eddy simulation of separated flow over a swept wing with approximate near wall modelling, Aeronaut J, November 2007, 111, (1125), pp 689697.Google Scholar
9. Li, N. and Leschziner, M.A. Large-eddy simulation of flow over a swept wing with approximate near wall modelling, AIAA, January 2007, Paper 2007-1118.Google Scholar
10. Hahn, M. and Drikakis, D. Implicit large-eddy simulation of swept-wing flow using high-resolution methods. AIAA J, March 2009, 47, (3), pp 618630.Google Scholar
11. Lawson, N.J. The application of laser measurement techniques to aerospace flows, Proceedings of the I MECH E Part G J Aerospace Eng, 218, (1), 1 January 2004, pp 3357(25).Google Scholar
12. Gleyzes, C. and Capbern, P. Experimental study of two Airbus/ONERA airfoils in near stall conditions. Part I: boundary layers. Aerospace Science and Technology, 2003, 7, pp 439449.Google Scholar
13. Ericsson, L.E. and King, H. Effect of leading-edge geometry on delta wing unsteady aerodynamics, J Aircr, 1992, 30, (5), pp 793795.Google Scholar
14. McParlin, S.J. Private communication – detailed designs for two swept wing models with 40° and 60° angles of sweep. Qinetiq, 2003.Google Scholar
15. Jaryczewski, R. 2005, Private communication.Google Scholar
16. Schlichting, H. and Gersten, K. Boundary Layer Theory, McGraw-Hill, New York, USA, 2000, 8th ed, p 441.Google Scholar
17. Schaeffler, N.W. and Jenkins, L.N. Isolated synthetic jet in cross flow: experimental protocols for a validation dataset, AIAA J, 2006, 44, (12), pp 28462856.Google Scholar
18. Edwards, R.V. Report of the special panel on statistical particle bias problems in laser anemometry, ASME, Transactions, J Fluids Engineering (ISSN 0098-2202), June 1987, 109, p 89.Google Scholar
19. Bremhorst, K. and Hollis, P.G. Velocity field of an axisymmetric pulsed, subsonic, air jet. AIAA J, 1990, 28, (12), pp 20432049.Google Scholar