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Two-dimensional potential method simulations of a body-strake configuration

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


C. Toomer

Sean Tuling
Senior Lecturer in Aerospace Engineering

L. Dala


The lee-side flow over a cruciform wing-body configuration at supersonic speeds in the "+" orientation up to angles of 25 deg have been simulated using the single concentrated vortex and discrete vortex model methods. The wings or strakes are of very low aspect ratio of order 0.025 with taper ratio ≈1 with a length of 11.25 Dmounted on a 19D tangent ogive body. The simulations revealed that the single concentrated vortex model is only suitable at low angles, while the discrete vortex model can predict both the flowfield and normal force reasonably when the lee-side boundary-layer separation characteristics are modeled. The resulting secondary vortex due to the wing-body junction has been identified to significantly influence the lee-side flow topology, and its exclusion results in higher normal forces and incorrect prediction of vortex positions. Copyright © 2013 by the American Institute of Aeronautics and Astronautics, Inc.


Toomer, C., Tuling, S., Dala, L., & Toomer, C. (2014). Two-dimensional potential method simulations of a body-strake configuration. Journal of Spacecraft and Rockets, 51(2), 468-477.

Journal Article Type Article
Publication Date Jan 1, 2014
Journal Journal of Spacecraft and Rockets
Print ISSN 0022-4650
Publisher American Institute of Aeronautics and Astronautics
Peer Reviewed Peer Reviewed
Volume 51
Issue 2
Pages 468-477
Keywords body-strake configuration, simulation
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