COMPARISON OF PLANAR FLUORESCENCE MEASUREMENTS AND COMPUTATIONAL MODELING OF SHOCK-LAYER FLOW

Planar laser-induced fluorescence is used to image transient and quasi steady flow phenomena associated with an impulsively started supersoni c jet incident on a circular cylinder. The transient phenomena observe d are consistent with established theoretical work on the development of nozzle flows in a shock tunnel and with well understood shock refle ction processes. The technique is also used to measure the rotational temperature in the jet and in the shock layer on the cylinder after th e establishment of quasisteady Bow conditions. The inviscid how betwee n the bow shock and the edge of the boundary layer and the viscous flo w within the boundary layer are modeled numerically using an iterative scheme. Good agreement is achieved between the computational and expe rimental results for most of the imaged field, except for the region n ear the shock vertex, where Bow nonuniformities near the centerline pe rturb the shock from the shape expected for a uniform incident flow.