Shock effects on Delta Wing Vortex breakdown

Schiavetta, L.A., Boelens, O.J., Crippa, S., Cummings, R.M., Fritz, W. and Badcock, K.J. (2009) Shock effects on Delta Wing Vortex breakdown. Journal of Aircraft, 46(3), pp. 903-914. (doi:10.2514/1.38792)

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Publisher's URL: http://dx.doi.org/10.2514/1.38792

Abstract

It has been observed that delta wings placed in a transonic freestream can experience a sudden movement of the vortex breakdown location as the angle of incidence is increased. The current paper uses computational fluid dynamics to examine this behavior in detail. The study shows that a shock/vortex interaction is responsible. The balance of the vortex strength and axial flow and the shock strength are examined to provide an explanation of the sensitivity of the breakdown location. Limited experimental data are available to supplement the computational fluid dynamics results in certain key respects, and the ideal synergy between computational fluid dynamics and experiments for this problem is considered.

Item Type:Articles
Status:Published
Refereed:Yes
Glasgow Author(s) Enlighten ID:UNSPECIFIED
Authors: Schiavetta, L.A., Boelens, O.J., Crippa, S., Cummings, R.M., Fritz, W., and Badcock, K.J.
College/School:College of Science and Engineering > School of Engineering > Aerospace Sciences
Journal Name:Journal of Aircraft
ISSN:0021-8669
Published Online:01 January 2009

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