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Experimental and computational analysis of a tangent ogive slender body at incompressible speeds

Schoombie, Janine; Tuling, Sean; Dala, Laurent


Janine Schoombie

Sean Tuling
Senior Lecturer in Aerospace Engineering

Laurent Dala


© 2017 Elsevier Masson SAS A combined computational and experimental analysis was performed on a tangent ogive body with very low aspect ratio wings in the ‘+’ (plus) orientation at Mach numbers 0.1, 0.2 and 0.3, with the aim of developing a database of global force and moment loads. Three different span to body diameter ratios were tested with aspect ratios of 0.022, 0.044 and 0.067. Aerodynamic loads were obtained and flow visualization was performed to gain an understanding of the lee side flow features. It was found that the global loads were independent of Mach number as is expected at incompressible speeds. The numerical centre-of-pressure predictions were validated experimentally for angles of attack higher than 6 degrees. The correlation below 6 degrees was only reasonable due to the relative higher balance uncertainties. Vortex separation was observed for all three span to body diameter configurations, whose locations did not correlate to that of an impulsively started flow for a flat plate. This indicated possible configuration specific phenomena or body-wing interactions.


Schoombie, J., Tuling, S., & Dala, L. (2017). Experimental and computational analysis of a tangent ogive slender body at incompressible speeds. Aerospace Science and Technology, 69, 474-484.

Journal Article Type Review
Acceptance Date Jun 10, 2017
Publication Date Oct 1, 2017
Journal Aerospace Science and Technology
Print ISSN 1270-9638
Publisher Elsevier
Peer Reviewed Peer Reviewed
Volume 69
Pages 474-484
Keywords slender body, CFD, experimental, very low aspect ratio wings
Public URL
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