WHEN A finite span lifting wing is located in a uniform flow, trailing vortices are generated by the wing. It is well known from the Kelvin theorem that the trailing vortex strength is proportional to the spanwise slope of the bound vortex distribution. When the wing is located in a nonuniform flow, the problem becomes complex. Such flow has been dealt with by Vandry [1], 2 Karman and Tshen [2], Honda [8], and Smith [4]. It has been found that this flow has an extra trailing vortex created by the interaction between the nonuniform flow and the wing. This extra vortex is called the secondary vortex and has been studied extensively in connection with the theory of turbomachinery.

Keywords:
thin foil, Theorem, secondary vortex, Turbomachinery, formula, kutta joukowsky theorem, vortice, propeller theory, vortex strength, nonuniform flow
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1988. The Society of Naval Architects and Marine Engineers
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