Surface shaping to suppress vortex breakdown on delta wings

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Surface shaping to suppress vortex breakdown on delta wings

Srigrarom, S. / Kurosaka, M.

In an accompanying Note (AIAA Journal, Vol. 38, No. 1, 2000, pp. 183-186) evidence of vortex- breakdown suppression is presented by reconfiguring the planform of a delta wing from straight leading edges to a shaped form. The underlying rationale for such a change in wing geometry is based on the so-called self-induction mechanism of vortex breakdown for the straight leading edge: in the transient formative stage of vortex breakdown, self-induction in the shear layers spiraling around the straight vortex core causes the pile up of vorticity, which in turn induces backflow and radial enlargement of stream surfaces. If the proposed self-induction mechanism of vortex breakdown, which hinges on the straightness of the vortex core, is indeed correct, one may be able to suppress the vortex breakdown by forcing the path of the core to deviate from a straight line . In the preceding Note this was achieved by shaping the leading edge of a delta wing that resulted in a spanwise perturbation to the vortex core. Even for a delta wing with straight leading edges, a requisite disturbance may be generated by wing surface shaping or bulges. Such bulges would create a perturbation normal to the wing surface, which induces similar deviation of the core from a straight line. The effectiveness of such surface bulges in inducing vortex breakdown is illustrated in this Note.