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Abstract
Results of zero-lift drag characteristics of afterbodies with a square base relevant to missile and projectile applications at several transonic Mach numbers and Mach 2 are presented. These afterbodies, at zero incidence, generate vortical flows upstream of the base like that on the lee side of a delta wing at incidence. The measurements made consisted primarily of afterbody drag using a balance and base pressure and extensive surface flow visualization studies were carried out to infer features associated with vortex flows. Results of base pressure, boat-tail profile drag, and total afterbody drag are presented and compared with results from the axisymmetric counterpart involving circular arc and conical boat tailing having the same base area. Some aspects of the flow features on square-base afterbodies are discussed as well.
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