Abstract
A method has been proposed of controlling separated base flows as a means of reducing aerodynamic drag. A series of steps attached to the base of the body of interest is used to control flow separation by forming a system of captive vortices on the steps. Kentfield's wind tunnel experiments seemed to confirm this concept for axisymmetric bodies at low subsonic Mach numbers and low Reynolds numbers. He reported drag reductions of as much as 56% using stepped afterbodies as compared to identical bodies with flat bases. The paper presents results obtained from further investigations of this stepped base concept in conjunction with both fin- and spin-stabilised configurations at high subsonic,
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