ESDU 70009@ which is one of a series of four@ presents data for the deflection of a streamline in the conical flow field between the shock and the surface of a sharp-nosed right-circular cone at zero incidence in a uniform@ inviscid@ supersonic airflow. The data are given for upstream Mach numbers increasing from the shock detachment value to a value of 4 for cones with semi-vertex angles of 5@ 10@ 15@ 20@ 25@ 30@ 40 and 50 degrees and were obtained from an exact solution of the conical flow equations.