Two-Dimensional Potential Method Simulations of a Body–Strake Configuration

S. Tuling, L. Dala, C. Toomer

Research output: Contribution to journalArticlepeer-review

3 Citations (Scopus)


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 11.25D mounted 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.
Original languageEnglish
Pages (from-to)468-477
JournalJournal of Spacecraft and Rockets
Issue number2
Publication statusPublished - 1 Mar 2014


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