Abstract
*† The paper describes an experimental study of the effects of sideslip on the flow over a 65-deg swept delta wing at an angle of attack of 30 deg. At this angle the major part of the flow over the wing is affected by vortex core breakdown. Sideslip causes a strong asymmetry in the location of the vortex breakdown point and is shown to have a significant effect on the topology of the surface flow. Special attention is paid to the flow on the apex of the delta wing. The flow on this part of the wing is poorly resolved in the experiment. A large-scale model of the apex has been constructed to improve the resolution of the flow. Flow visualization tests provide detailed information on the asymmetric flow topology on the apex caused by sideslip effects.
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