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

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 o...

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Bibliographic Details
Published in:Aerospace science and technology 2013-08, Vol.29 (1), p.373-385
Main Authors: Tuling, S., Dala, L., Toomer, C.
Format: Article
Language:English
Subjects:
Circularity
Cross flow
Cruciform wings
Exact sciences and technology
Fluid dynamics
Fundamental areas of phenomenology (including applications)
Mach number
Physics
Rotational flow and vorticity
Separated flows
Slender bodies
Supersonic aircraft
Symmetric vortices
Symmetry
Tangents
Very low aspect ratio wings
Vortex shedding
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Summary: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.
ISSN:1270-9638
1626-3219
DOI:10.1016/j.ast.2013.04.008