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Some compressibility effects on the lee side flow structures of cruciform wing–body configurations with very low aspect ratio wings

Tuling, S.; Toomer, C.; Tuling, Sean; Toomer, Chris; Dala, L.

Authors

Sean Tuling Sean.Tuling@uwe.ac.uk
Senior Lecturer in Aerospace Engineering

C. Toomer

Sean Tuling

L. Dala



Abstract

A series of validated numerical simulations of a tangent ogive circular body in combination with very low aspect ratio cruciform wings at supersonic Mach numbers and angles of attack up 25° have been performed. Inspection of the flow in the cross flow planes revealed that symmetric vortex shedding occurs when the cross flow velocity is supersonic not only in the accelerated flow region outside the vortices, but in particular, the reverse flow in the recirculation region. Symmetric vortex shedding occurs for tangent ogive bodies at cross flow Mach numbers greater than 0.65, and for circular bodies with cruciform wings in the ‘+’ orientation and span to body diameter ratios of 1.25 at cross flow Mach numbers greater than 0.55.

Citation

Tuling, S., Dala, L., & Toomer, C. (2013). Some compressibility effects on the lee side flow structures of cruciform wing–body configurations with very low aspect ratio wings. Aerospace Science and Technology, 29(1), 373-385. https://doi.org/10.1016/j.ast.2013.04.008

Journal Article Type Article
Publication Date Aug 1, 2013
Journal Aerospace Science and Technology
Print ISSN 1270-9638
Publisher Elsevier
Peer Reviewed Peer Reviewed
Volume 29
Issue 1
Pages 373-385
DOI https://doi.org/10.1016/j.ast.2013.04.008
Keywords symmetric vortices, vortex shedding, slender bodies, very low aspect ratio wings
Public URL https://uwe-repository.worktribe.com/output/929544
Publisher URL http://dx.doi.org/10.1016/j.ast.2013.04.008