Hostname: page-component-cd9895bd7-dk4vv Total loading time: 0 Render date: 2024-12-28T04:36:11.904Z Has data issue: false hasContentIssue false
  • English
  • Français

Prediction of tunnel wall upwash for delta wings including vortex breakdown effects

Published online by Cambridge University Press:  04 July 2016

L. W. Traub
L. W. Traub*
Affiliation:
Aerospace Engineering DepartmentTexas A&M University, Texas, USA
Get access Rights & Permissions [Opens in a new window]

Abstract

An incompressible method is presented to predict the upwash corrections associated with vortical flow as a result of wind-tunnel side wall effects. An image system is used to simulate the tunnel side walls which are assumed to be solid. An integral expression is formulated, representing the average upwash induced over the wing by the image system. Wall effects may be determined for flows with and without vortex breakdown. Comparisons of the results with upwash predictions from a Navier-Stokes study show close accord. The upwash expression also displayed the ability to successfully predict corrections for flows involving vortex breakdown.

Type
Research Article
Information
The Aeronautical Journal , Volume 103 , Issue 1021 , March 1999 , pp. 139 - 142
Copyright
Copyright © Royal Aeronautical Society 1999 

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. Ericsson, L.E. Slender wing rock revisited, J Aircr, 1993, 30, (3), pp 352–356.Google Scholar
2. Pope, A. and Rae, W.H. Low Speed Wind Tunnel Testing, Wiley, New York, 1984, pp 199–208, 362–424.Google Scholar
3. Maskell, E.C. A theory on the blockage effects on bluff bodies and stalled wings in a closed wind tunnel, British Aeronautical Research Council, 1963, R&M 3400.Google Scholar
4. Proctor, J.G. Wall pressure signature wind-tunnel wall constraint correction methods, British Aerospace, 1984, BAe-ARG-188, April.Google Scholar
5. Ashill, P.R. and Keating, R.F.A. Calculation of tunnel wall interference from wall-pressure measurements, Aeronaut J, January 1988, 92, (911), pp 36–53.Google Scholar
6. Frink, N.T. Computational study of wind tunnel wall effects on flow field around delta wings, AIAA Paper 87–2420, August 1987.Google Scholar
7. Vatsa, V.N. and Wedan, B.W. Effect of sidewall boundary layer on a wing in a wind tunnel, J Aircr, 1989, 26, (2), pp 157–161.Google Scholar
8. Hsing, C.C.A. and Lan, C.E. Low speed wall interference assessment/correction with vortex flow effect, J Aircr, 1997, 34, (2) pp 220–227.Google Scholar
9. Weinberg, Z. Effect of tunnel walls on vortex breakdown location over delta wings, AIAA J, 1992, 30, (6), pp 1584–1586.Google Scholar
10. Pelletier, A. and Nelson, R.C. Factors influencing vortex breakdown over 70° delta wings, AIAA Paper 95–3469, Aug. 1995.Google Scholar
11. Elle, B.J. and Jones, J.P. A note on the vorticity distribution on the surface of slender delta wings with leading edge separation, J RAeS, March 1961, 65, pp 195–198.Google Scholar
12. Mangler, K.W. and Smith, J.H.B. Calculation of the flow past slender delta wings with leading edge separation, RAE Report Aero 2593, 1957, May.Google Scholar
13. Lowson, M. Visualization measurements of vortex flows, J Aircr, 1991, 28, (5), pp 320–327.Google Scholar
14. Traub, L.W. Prediction of delta wing leading-edge vortex circulation and lift-curve slope, J Aircr, 1997, 34, (3), pp 450–452.Google Scholar
15. Lambourne, N.C. and Bryer, D.W. The bursting of leading edge vortices — some observations and discussion of the phenomenon, Aeronautical Research Council, 1961, R&M 3282, London, April.Google Scholar
16. Traub, L.W. Simple prediction method for location of vortex break down on delta wings, J Aircr, 1996, 33, (2), pp 452–454.Google Scholar
17. Traub, L.W. Prediction of vortex breakdown and longitudinal characteristics of swept slender planforms, J Aircr, 1997, 34, (3), pp 353–359.Google Scholar