A three-dimensional viscous flow analysis is performed using a time-marching Reynolds-averaged Navier-Stokes code for a 3:1 rectangular nozzle with two delta tabs located at the nozzle exit plane to enhance mixing. Two flow configurations, a subsonic jet case and a supersonic jet case using the same tab configuration, which were previously studied experimentally, are computed and compared with the experimental data. The experimental data include streamwise velocity and vorticity distributions for the subsonic case, and Mach number distributions for the supersonic case, at various axial locations downstream of the nozzle exit. The computational results show very good agreement with the experimental data. In addition, the effect of compressibility on vorticity dynamics is examined by comparing the vorticity contours of the subsonic jet case with those of the supersonic jet case which were not measured in the experiment.
Computation of Three-Dimensional Compressible Flow From a Rectangular Nozzle With Delta Tabs
Reddy, D. R., Steffen, C. J., Jr., and Zaman, K. B. M. Q. (April 1, 1999). "Computation of Three-Dimensional Compressible Flow From a Rectangular Nozzle With Delta Tabs." ASME. J. Eng. Gas Turbines Power. April 1999; 121(2): 235–242. https://doi.org/10.1115/1.2817111
Download citation file: