IHS ESDU Inviscid supersonic flow past cones at zero incidence: (ii) surface pressure coefficient and shock angle for circular cones. AERO S.00.03.13

ESDU AERO S.00.03.13, which is one of a group of four, presents data for the surface pressure coefficient on a sharp-nosed right-circular cone. The data are given in graphical form for upstream Mach numbers from 1 to 4 for cones with semi-vertex angle from 0 to 42.5 degrees and were obtained from an exact solution of the conical flow equations. They apply only when the flow is fully supersonic and a curve is given defining the limit when the flow on the cone is just at a Mach number of unity.