Flow Visualizations and Measurements of a Three-Dimensional Supersonic Separated Flow

摘要

The flow along the afterbody and in the base region of a circular cylinder with a length-to-radius ratio of 3.0 aligned at a 10-deg angle of attack to a nominal Mach 2.5 freestream has been investigated experimentally. The ]objective is to better understand the mechanisms that control base flow for supersonic bodies with a nonzero- angle-of-attack orientation. Laser Doppler velocimety measurements were conducted in the incoming boundary layer to quantify the initial conditions at the onset of three-dimensional behavior.