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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
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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 

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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