ESDU AERO S.00.03.13:1975
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Inviscid supersonic flow past cones at zero incidence: (ii) surface pressure coefficient and shock angle for circular cones
| Published By | Publication Date | Number of Pages |
| ESDU | 1975-05-01 | 4 |
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.
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