An experimental program using a 9.7 deg half-angle cone model at free stream Mach number equals 4.88 and alpha prime S of 10 deg and 29.5 deg

The flow field of a blunted cone model at supersonic speeds is described. The data consist of surface pressure measurements, surface oil flow photographs, and schlieren photographs. The tests were conducted in a two-dimensional, blow down type wind tunnel, using air as a test gas. A mercury filled manometer board was used to measure model surface pressure data.