Numerical and Experimental Studies on Supersonic Free Jet with Various Cross-Sectional Tab Configuration

Supersonic free jet studies were made with tabbed nozzle configurations having different cross-sections. Experimental and numerical simulations were adopted to obtain the basic flow field features. Pitot tube measurements and Schlieren flow visualization were carried out in experiments, whereas an in-house build, 3D-Euler flow solver was used to obtain the results. The results obtained from the investigation show the basic flows indicating shock distortion, Mach disk location, reduction in core length of the jet, and other features for tabbed configuration.