Experimental Studies of Supersonic Flow past a Circular Cylinder

Experimental studies using shock tubes are presented of the mixed Type flow around a circular cylinder placed normal to the general flow of Mach number 1.35, 1.8, 2.7, 3.5, 4.0, and 6.0. With the Mach-Zehnder interferometer and schlieren method the followings were measured: a) shape of detached shock wave, b) distance d of shock wave from the cylinder nose, c) pressure coefficient C p on the surface of the cylinder, d) density distribution behind the detached shock, e) streamlines in subsonic region.