The Taylor-Maccoll theory, dealing with the aerodynamic problem of the flow around a cone moving without yaw at supersonic speeds through air, is extended. The theory is applied to the case in which the cone is moving with a small yaw. The problem is reduced to a form suitable for computation, and the theory is checked by comparing its predictions about the shape and yaw of the shock wave with experiment. The head contribution to the total normal-force coefficient and center of pressure of a conical headed projectile in flight is determined.