Abstract
The flow region round a circular cylinder with tangential injection of air immersed in a uniform flow is divided into four parts that are parts of curved wall-jet, turbulent boundary layer, laminar boundary layer and wake. The characteristics of each part are calculated by the authors' method on the curved wall-jet, Furuya's method on the turbulent boundary layer and Thwaites' method on the laminar boundary layer. Based upon these characteristics obtained, the aerodynamic forces are calculated and compared with the authors' experiment. It was found that, when one parameter among the lift coefficient, the drag coefficient, the front stagnation-point, the separation point of jet and the base-pressure coefficient was given, the rest of them are uniquely determined.
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