AN EXPERIMENTAL INVESTIGATION OF THE RELATION BETWEEN SKIN FRICTION AND HEAT TRANSFER ON THE SURFACE OF A SPHERE AT SUPERSONIC SPEEDS. PART I. PRESSURE DISTRIBUTION AND BOUNDARY LAYER MEASUREMENTS ON A SPHERE.
DAVID TAYLOR MODEL BASIN WASHINGTON D C
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In order to design a balance mechanism capable of measuring the skin-friction drag on a small surface element of a sphere subjected to supersonic flow, it was necessary to determine the order of magnitude of the skin-friction and pressure loads on such an element. To this end, wind tunnel tests were conducted, principally at a Mach number of 2.86, on a 3-inch-diameter sphere and hemisphere to measure the boundary-layer characteristics at one point and to determine the pressure distribution. From these measurements, approximate maximum steady-state friction and pressure loads were determined which will be used as starting points for the design of a skin-friction balance. Author