Hostname: page-component-745bb68f8f-b95js Total loading time: 0 Render date: 2025-02-03T10:13:45.193Z Has data issue: false hasContentIssue false
  • English
  • Français

Alleviation of pitch-up on delta wings using distributed porosity

Published online by Cambridge University Press:  04 July 2016

L. W. Traub ,
B. Moeller  and
S. F. Galls
L. W. Traub
Affiliation:
Aerospace Engineering Department, Texas A&M University, Texas, USA
B. Moeller
Affiliation:
Aerospace Engineering Department, Texas A&M University, Texas, USA
S. F. Galls
Affiliation:
Aerospace Engineering Department, Texas A&M University, Texas, USA
Get access Rights & Permissions [Opens in a new window]

Abstract

An experimental investigation was undertaken to determine the effectiveness of distributed surface porosity for the alleviation of pitch-up on a delta wing. Tests were undertaken using a 65° sweep delta wing with distributed porosity evaluated at various locations on the wing. Force balance, on and off surface flow visualisation and flow field surveys using a multi-hole probe were undertaken. The data shows that distributed porosity applied along the wing leading edge at the apex is effective in eliminating pitch-up whilst incurring a minimal performance cost. Trailing edge porosity generally degraded performance.

Type
Research Article
Information
The Aeronautical Journal , Volume 103 , Issue 1025 , July 1999 , pp. 339 - 347
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. Benoliel, A.M. and Mason, W.H. Pitch-up characteristics for HSCT class planforms: survey and extension, AIAA Paper 94-1819, January 1994.Google Scholar
2. Rao, D.M. and Johnson, T.H. Alleviation of the subsonic pitch-up of delta wings, J Aircr, 1983, 20, (6), pp 530–535.Google Scholar
3. Hoffler, K.D. and Rao, D.M. An investigation of the tabbed vortex flap, J Aircr, 1985, 22, (6), pp 490–497.Google Scholar
4. Traub, L.W. Efficient lift enhancement of a blunt edged delta wing, Aeronaut J, 1997, 101, (1009), pp 439–445.Google Scholar
5. Shindo, S. Simplified tunnel correction method, J Aircr, 1995, 32, (4), pp 210–213.Google Scholar
6. Rae, W.H. and Pope, A. Low-Speed Wind Tunnel Testing, Wiley, New York, 1984, pp 199–208, 362–424.Google Scholar
7. Kirkpatrick, D.L.I. Analysis of the Static Pressure Distribution on a Delta Wing in Subsonic Flow, ARC, R & M 3619, 1970, London.Google Scholar
8. Lambourne, N.C. The Breakdown of Certain Types of Vortex, ARC, CP915, 1967, London.Google Scholar
9. Lambourne, N.C. and Bryer, D.W. The Bursting of Leading-Edge Vortices — Some Observations and Discussion of the Phenomenon, ARC, R & M 3282, 1961, London.Google Scholar
10. Traub, L.W. Simple prediction method for location of vortex breakdown on delta wings, J Aircr, 1996, 33, (2), pp 452–454.Google Scholar
11. Traub, L.W. Prediction of vortex breakdown and longitudinal characteristics of swept slender planforms, J Aircr, 1997, 34, (3), pp 353–359.Google Scholar
12. Traub, L.W. and Moeller, B. LOW Reynolds number effects on delta wing aerodynamics, J Aircr, 1998,35, (4), pp 653–656.Google Scholar
13. Washburn, A.E. Effects of external influences on subsonic delta wing vortices, AIAA Paper 92-4033, Tennessee, July 1992.Google Scholar
14. Visbal, M.R. and Gordnier, R.E. Origin of computed unsteadiness in the shear layer of delta wings, J Aircr, 1995, 32, (5), pp 1146–1148.Google Scholar
15. 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
16. Kegelman, J.T. and Roos, F.W. The flowfields of bursting vortices over moderately swept delta wings, AIAA Paper 90–0599, January 1990.Google Scholar