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Prediction of vortex lift of non-planar wings by the leading-edge suction analogy

Published online by Cambridge University Press:  04 July 2016

B. C. Hardy  and
S. P. Fiddes
B. C. Hardy
Affiliation:
Aerodynamics Department, Royal Aircraft Establishment, Farnborough
S. P. Fiddes
Affiliation:
Aerodynamics Department, Royal Aircraft Establishment, Farnborough
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Summary

A three-dimensional panel method has been used to calculate edge-suction forces for thin sharp-edged wings in incompressible flow. The suction forces have been used to estimate the vortex lift on the wings by means of the leading-edge suction analogy due to Polhamus.

The results for planar wings are in acceptable agreement with other methods based on the suction analogy. A limited comparison with results from experiments for non-planar wings revealed good prediction of lift and drag increments associated with the deflection of leading and trailing edge flaps for ‘conventional’ wings of high sweep, but only moderate agreement for a grossly non-planar configuration.

Type
Research Article
Information
The Aeronautical Journal , Volume 92 , Issue 914 , April 1988 , pp. 154 - 164
Copyright
Copyright © Royal Aeronautical Society 1988 

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Footnotes

*

Now in the Department of Aerospace Engineering, University of Bristol.

References

1. Stanbrook, A. and Squire, L. C. Possible types of flow at swept leading-edges. Aeronaut Q, 1964, 15, 77–82.Google Scholar
2. Moir, I. R. M. and Fiddes, S. P. Unpublished MoD(PE), 1985.Google Scholar
3. Hoeijmakers, H. W. M. and Rizzi, A. Vortex-fitted potential and vortex-captured Euler solutions for leading-edge vortex flow. AIAA J, 1985, 23, 1983–1985.Google Scholar
4. Johnson, F. T., Lu, P., Tinoco, E. N. and Epton, M. A. An improved panel method for the solution of three-dimensional leading-edge vortex flows. Volume 1, Theory Document, NASA CR 3278, 1980.Google Scholar
5. Polhamus, E. C. A concept of the vortex lift of sharp-edged delta wings based on a leading-edge suction analogy. NASA TN D-3767, 1966.Google Scholar
6. Lamar, J. E. and Herbert, H. E. Production version of the extended NASA Langley vortex lattice FORTRAN computer program. Volume 1, Users Guide, NASA TM 83303, 1982.Google Scholar
7. Petrie, J. A. H. A surface source and vorticity panel method. Aeronaut Q, 1978, 29, 251–269.Google Scholar
8. Lamar, J. E. Extension of the leading-edge suction analogy to wings with separated flow around the side edges at subsonic speeds. NASA TR R-428, Oct. 1974.Google Scholar
9. Lan, C. E. and Mehrotra, S. C. An improved Woodward's panel method for calculating leading-edge and side-edge suction forces at subsonic and supersonic speeds. NASA CR 3205, 1979.Google Scholar
10. Garner, H. C. On the application of subsonic wing theory to edge forces and roll-rate derivatives. RAE Technical Report 73003, 1977.Google Scholar
11. Kulfan, R. M. Wing geometry effects on leading-edge vortices. AIAA Paper 79-1872, 1979.Google Scholar
12. Ward, G. N. Linearised theory of steady high-speed flow. Cambridge University Press, 1955.Google Scholar
13. Lan, C. E. and Hsu, C. H. Effects of vortex breakdown on longitudinal and lateral-directional aerodynamics of slender wings by the suction analogy. AIAA Paper 82-1385, 1982.Google Scholar
14. Wentz, W. H. JR, and Kohlman, D. L. Vortex breakdown on slender sharp-edged wings. AIAA Paper 69-778, 1969.Google Scholar
15. Wentz, W. H. JR. Wind tunnel investigations of vortex break down on slender sharp-edged wings. PhD Thesis, University of Kansas, 1968 (See also NASA CR-98737).Google Scholar
16. Lamar, J. E. Recent studies of subsonic vortex lift including parameters affecting stable leading-edge vortex flow. J Aircr, 1977, (4), 1205–1211.Google Scholar
17. Riley, N. and Smith, J. H. B. Prediction of leading-edge vortex behaviour to supplement the suction analogy. J Eng Math, 1985, 19, 157–172.Google Scholar
18. Sells, C. C. L. An iterative procedure for calculation of the loading on a thin unswept wing. RAE Technical Report 72009, 1972.Google Scholar
19. Lamar, J. E. and Gloss, B. B. Subsonic aerodynamic characteristics of interacting lifting surfaces with separated flow around sharp edges predicted by a vortex lattice method. NASA TN D-7921, 1975.Google Scholar
20. Woodward, F. A. Analysis and design of wing-body combinations at subsonic and supersonic speeds. J Aircr,1968, (5), 528–534.Google Scholar
21. Quinto, P. F. and Paulson, J. W. Flap effectiveness on subsonic longitudinal aerodynamic characteristics of a modified arrow wing. NASA TM 84582. 1983.Google Scholar
22. Grantz, A. C. The lateral directional characteristics of a 74 degree delta wing employing gothic planform vortex flaps. NASA CR 3848, Nov. 1984.Google Scholar
23. MoD Unpublished.Google Scholar