Abstract
A method to predict nose vortex shedding from circular and noncircular slender bodies in supersonic flow at angles of attack and roll is presented. The body is represented by a supersonic panel method, and the lee side vortex wake is modeled by discrete vortices in cross-flow planes. The three-dimensional steady flow problem is reduced to a two-dimensional, unsteady, separated flow problem for solution. Comparison of measured and predicted surface pressure distributions, flowfield surveys, and aerodynamic characteristics are presented for circular and elliptic bodies. Good agreement between experiment and theory for a range of flow conditions indicate that the principal features of the flow phenomena are modeled correctly.
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