Abstract
The effects of sideslip on the flow over a flat-plate 65-deg swept delta wing tested at a geometric angle of attack of 30 deg are described. At this angle of attack, the major part of the flow over the wing is affected by vortex core breakdown. Sideslip causes a strong asymmetry in the breakdown location. This is shown to have a large effect on the surface flow and pressures, and on the normal-force and pitching-moment coefficient.
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