Summary
The breakdown of the primary vortex forming over a 70°-sweep angle delta wing has been investigated at a velocity of 24 m/s, the angle of incidence being 26°. Detailed velocity measurements in the breakdown region have been executed by means of a three component LDV system to allow an accurate definition of the mean flow structure in planes normal to the delta wing upper surface. The topology of these transverse fields is characterized by the existence of limit circles in the pattern of the lines of force of the projected vector field. The obtained results tend to show that, in spite of its spectacular aspect, the breakdown weakly affects the flow structure in the immediate vicinity of the wing surface.
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© 1994 Springer-Verlag
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Délery, J., Molton, P. (1994). Topology of the flow resulting from vortex breakdown over a delta wing at subsonic speed. In: Schnerr, G.H., Bohning, R., Frank, W., Bühler, K. (eds) Fluid- and Gasdynamics. Acta Mechanica, vol 4. Springer, Vienna. https://doi.org/10.1007/978-3-7091-9310-5_33
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DOI: https://doi.org/10.1007/978-3-7091-9310-5_33
Publisher Name: Springer, Vienna
Print ISBN: 978-3-211-82495-5
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