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DNS of aircraft wake vortices: the effect of stable stratification on the development of the Crow instability

DNS of aircraft wake vortices: the effect of stable stratification on the development of the Crow instability
DNS of aircraft wake vortices: the effect of stable stratification on the development of the Crow instability
A numerical experiment is performed to determine the likelihood that the Crow instability will mitigate the potentially hazardous effects of the buoyancy-induced rebound of initially parallel line vortices. Parameters are chosen to correspond to wake vortices downstream of an elliptically loaded wing with large span (typical of the A380) landing in very stable conditions. The DNS is initiated by perturbing the vortex pair into the shape of the linearly most unstable Crow eigenmode, with a maximum displacement of 1% of the initial distance between the pair. Under these conditions, the Crow instability progresses fast enough to break the two dimensionality of the vortex system before it returns to its original elevation. This suggests that in many cases the Crow instability will prevent the rebounding vorticity from being a serious danger to following aircraft. Whether or not this will always happen in practice is an open question, requiring further investigation
9789048136520
7
519-525
Springer
Coleman, G.N.
ea3639b9-c533-40d7-9edc-3c61246b06e0
Johnstone, R.
8ac02aa2-776b-4f80-b44d-1a5cf8682f21
Yorke, C.P.
16edb777-ac59-4a85-bfb3-a23f89de26e3
Castro, I.P.
66e6330d-d93a-439a-a69b-e061e660de61
Armenio, Vincenzo
Geurts, Bernard
Frolich, Jochen
Coleman, G.N.
ea3639b9-c533-40d7-9edc-3c61246b06e0
Johnstone, R.
8ac02aa2-776b-4f80-b44d-1a5cf8682f21
Yorke, C.P.
16edb777-ac59-4a85-bfb3-a23f89de26e3
Castro, I.P.
66e6330d-d93a-439a-a69b-e061e660de61
Armenio, Vincenzo
Geurts, Bernard
Frolich, Jochen

Coleman, G.N., Johnstone, R., Yorke, C.P. and Castro, I.P. (2010) DNS of aircraft wake vortices: the effect of stable stratification on the development of the Crow instability. Armenio, Vincenzo, Geurts, Bernard and Frolich, Jochen (eds.) In Direct and Large-Eddy Simulation VII. vol. 13, Springer. pp. 519-525 . (doi:10.1007/978-90-481-3652-0_75).

Record type: Conference or Workshop Item (Paper)

Abstract

A numerical experiment is performed to determine the likelihood that the Crow instability will mitigate the potentially hazardous effects of the buoyancy-induced rebound of initially parallel line vortices. Parameters are chosen to correspond to wake vortices downstream of an elliptically loaded wing with large span (typical of the A380) landing in very stable conditions. The DNS is initiated by perturbing the vortex pair into the shape of the linearly most unstable Crow eigenmode, with a maximum displacement of 1% of the initial distance between the pair. Under these conditions, the Crow instability progresses fast enough to break the two dimensionality of the vortex system before it returns to its original elevation. This suggests that in many cases the Crow instability will prevent the rebounding vorticity from being a serious danger to following aircraft. Whether or not this will always happen in practice is an open question, requiring further investigation

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More information

Published date: 2010
Venue - Dates: Proceedings of the Seventh International ERCOFTAC Workshop on Direct and Large-Eddy Simulation, Trieste, Italy, 2008-09-08 - 2008-09-10
Organisations: Aerodynamics & Flight Mechanics Group

Identifiers

Local EPrints ID: 300658
URI: http://eprints.soton.ac.uk/id/eprint/300658
ISBN: 9789048136520
PURE UUID: bb1588d8-518e-4bb9-ba3a-31b83b166c7f

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Date deposited: 29 Feb 2012 09:23
Last modified: 14 Mar 2024 10:26

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Contributors

Author: G.N. Coleman
Author: R. Johnstone
Author: C.P. Yorke
Author: I.P. Castro
Editor: Vincenzo Armenio
Editor: Bernard Geurts
Editor: Jochen Frolich

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