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RESEARCH PAPERS: Gas Turbines: Aircraft

Computation of Three-Dimensional Compressible Flow From a Rectangular Nozzle With Delta Tabs

[+] Author and Article Information
D. R. Reddy, C. J. Steffen, K. B. M. Q. Zaman

Turbomachinery and Propulsion Systems Division, NASA Lewis Research Center, MS 5-11, 21000 Brookpark Road, Cleveland, OH 44135

J. Eng. Gas Turbines Power 121(2), 235-242 (Apr 01, 1999) (8 pages) doi:10.1115/1.2817111 History: Received July 01, 1997; Online December 03, 2007

Abstract

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.

Copyright © 1999 by The American Society of Mechanical Engineers
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