Abstract: The purpose of this paper is to study the effect ofcable-mounting on flow over an afterbody of a aircraft. The experimentalresults show that: (1) the flow patterns over afterbody can be divided intoupper-separated, non-separated and under-separated type; (2) thecable influences the aerodynamic characteristics of the model by affectingthe vortex structure over it; (3) the basic flow patterns overafterbody have not been changed evidently by any of these three types ofcable-mounting configuration.