Experimental Investigation of Supersonic Gaseous Injection into a Supersonic Freestream

摘要

An experimental study of the mean and turbulent flowfield associated with low-angled supersonic gaseous injection into a supersonic freestream was performed. Air was injected at Mach 1.8, with an effective back pressure ratio of 3.0, through an orifice at an angle of 25 deg into a Mach 2.9 air freestream (Re/m=15*10~6). Cross-film anemometry and conventional mean flow probe surveys were acquired across the plume at two downstream stations (x/d=20 and 40). Schlieren photography was used for qualitative flow visualization. Turbulence measurements included contours of the turbulent kinetic energy and the full compressible Reynolds shear stresses in both the x-y and x-z planes.