Abstract
Abstract : An experimental investigation of supersonic flow around cones was conducted at a free stream mach number of 2.72 and Reynolds number per foot of 1660000. Three cones of semi-apex angles of 10 deg, 15 deg, and 10 deg were investigated at relative incidences up to 3. In addition to measuring surface pressure, a detailed study of the flow in the plane of symmetry phi = 180 deg was made by means of a pitot-hot wire probe. The shape of the outer shock wave as well as of the imbedded shocks were determined. Oil and vapor screen techniques and a Schlieren system were used to visualize the flow field.
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