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On wake vortex response for all combinations of five classes of aircraft

Published online by Cambridge University Press:  03 February 2016

L. M. B. C. Campos  and
J. M. G. Marques
L. M. B. C. Campos
Affiliation:
Secção de Mecânica Aeroespacial, Instituto Superior Técnico, Lisbon, Portugal
J. M. G. Marques
Affiliation:
Secção de Mecânica Aeroespacial, Instituto Superior Técnico, Lisbon, Portugal
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Abstract

The present paper concerns the response of a following airplane to a pair of wing tip vortices left by a leading aircraft, represented by the Hallock-Burnham model, including the effect of vorticity decay between the two aircraft. The effect of vorticity is evaluated in terms of the induced rolling moment and also the lift loss; these specify the roll acceleration and the downward acceleration, respectively. The corresponding two response equations can be put into the same dimensionless form, and integrated using exponential integrals. This specifies the roll rate and sink rate as a function of time; besides the latter, the bank angle and altitude loss, are also plotted, all also as a function of time, for all combinations of leading and following aircraft in five classes. These are the three ICAO weight categories of light, medium and heavy, plus two other cases, viz the special case of the Boeing 757, which requires larger separations distances, and the case of a future very large transport aircraft (VLTA) exceeding significantly the size of a Boeing 747.

Type
Research Article
Information
The Aeronautical Journal , Volume 108 , Issue 1084 , June 2004 , pp. 295 - 310
Copyright
Copyright © Royal Aeronautical Society 2004 

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References

1. Campos, L.M.B.C. and Marques, J.M.G. On the calculation of safe separation distances between aircraft due to turbulent wakes (in preparation), 2004.Google Scholar
2. Shen, S., Ding, F., Han, J., Lin, Y-L., Arya, S.P. and Proctor, F.H. Numerical modeling studies of wake vortices: real case simulations, 1999, AIAA Paper 99-0755, 37th Aerospace Sciences Meeting, Reno, Nevada.Google Scholar
3. Spalart, P.R. Airplane trailing vortices, 1998, Ann Rev Fluid Mech, 30, pp 107–138.Google Scholar
4. Rossow, V.J. Lift-generated vortex wakes of subsonic transport aircraft, 1999, Progr Aerosp Sci, 35, pp 507–660.Google Scholar
5. Hinton, D.A. An Aircraft Vortex Spacing System (AVOSS) for dynamical wake vortex spacing criteria, 1996, 78th Fluid Mechanics Panel & Symposium on the Characterization and modification of wakes from lifting vehicles in fluids, Trondheim, Norway.Google Scholar
6. Hinton, D.A., Charnock, J.K., Bagwell, D.R. and Grigsby, D. NASA aircraft vortex spacing system development status, 1999, AIAA 37th Aerospace Sciences Meeting, Reno, Nevada.Google Scholar
7. Jackson, W. (Ed) Wake vortex prediction: an overview, Appendix F: hazard definition, 2001, Transportation Department of Canada TP 13629E.Google Scholar
8. Abramowitz, M. and Stegun, I. Tables of Mathematical Functions, 1965, Dover, New York.Google Scholar
9. Hinton, D.A. and Tatnall, C.R. A candidate wake vortex strength definition for application to the NASA aircraft vortex space system (AVOSS), 1997, NASA Tech. Memo TM-110343.Google Scholar
10. Lamb, H. Hydrodynamics, 1932, Sixth edition, Cambridge University Press.Google Scholar
11. Hoffman, E.R. and Joubert, P.N. Turbulent line vortices, J Fluid Mech, 1963, 16, pp 395–411.Google Scholar
12. Hallock, J.N. and Burnham, D.C. Decay characteristics of wake vortex from jet transport aircraft, 1997, AIAA paper 97-0060, 35th Aerospace Science Meeting Exhibition, 9-10 Jan 1997, Reno, NV.Google Scholar
13. Proctor, F.H. The NASA-Langley wake vortex modeling effort in support of an operational aircraft spacing system, 1998, AIAA paper 98-0589.Google Scholar
14. Lighthill, M.J. An Informal Introduction to Fluid Mechanics, 1986 Oxford University Press.Google Scholar
15. Milne-Thomson, L.M. Theoretical Aerodynamics, 1958, Dover, New York.Google Scholar
16. Abott, I.H. and Doenhoff, A.E. Theory of Wing Sections, 1959, Dover, New York.Google Scholar
17. Tatnall, C.R. A Proposed Methodology for Determining Wake-Vortex Imposed Aircraft Separation Constraints, 1995, MSc thesis submitted at George Washington University.Google Scholar
18. Batchelor, G.K. Fluid Mechanics, 1967, Cambridge University Press.Google Scholar
19. Carslaw, H.S. and Jaeger, J.C. Heat Conduction in Solids, 1949, Oxford University Press.Google Scholar
20. Landau, L.D. and Lifshitz, E.F. Fluid Mechanics, 1953, Pergamon, Oxford.Google Scholar
21. Jackson, P. (Ed) Jane’s All-the-World’s Aircraft 2000-2001, 2000, MacDonald and Jane’s, London.Google Scholar
22. Stuerver, R.A. Airplane data base for wake-vortex hazard definition and assessment, 1995, Version 2.0, NASA Langley Research Center.Google Scholar
23. Hozäpfel, F. A probabilistic two-phase wake vortex decay and transport model, 2000, DLR Institut für Physik der Atmosphäre rep 163, Oberpfaffenhofen.Google Scholar
24. Campbell, S.D., Dasey, T.J., Freehart, R.E., Heinrichs, R.M., Matthews, M.P., Perras, G.H. and Rowe, G.S. Wake Vortex Filed Measurement Program at Memphis, TN, Data Guide, 1997, Lincoln Lab, Massachusetts Inst of Technology, Project Rep NASA/L-2, Cambridge, MA.Google Scholar