ESDU AERO S.00.03.16 provides graphs plotting against Mach number the value of the nose angle of a cone and of a two-dimensional wedge at which the nose shock is just detached from the nose, and similar graphs for the angle at which the flow behind the shock and on the surface of the cone and the wedge is just sonic. It is assumed that the ratio of the specific heat capacities of the air is 1.4. The curves are useful in assessing the limitations on the applicability of theories assuming completely supersonic flow on wings and bodies. Data for flow behind attached nose shocks are given in ESDU AERO S.00.03.09 to S.00.03.11 for wedges and in ESDU AERO S.00.03.13 and ESDU 70008, ESDU 70009 and ESDU 70010 for cones.