Corrugated Shifted Limiting Tabs’ Effectiveness on Supersonic Jet Mixing
Publication: Journal of Aerospace Engineering
Volume 31, Issue 2
Abstract
The mixing efficiency of a shifted limiting tab of a rectangular cross section, with corrugations all along its edges, placed downstream of a circular Mach 2 nozzle operated at different levels of expansion corresponding to nozzle pressure ratios (NPRs) 3–8 in steps of 1, has been studied experimentally. The corrugation geometries studied in this investigation are circular-arc and triangular. The corrugated tabs offered a geometrical blockage of 5% of the nozzle exit area for all the cases studied. The shifted positions studied are 0.25D, 0.5D, and 0.75D. In addition to shifted tabs, tabs at the nozzle exit (0D) are also studied for comparison. For the Mach 2 jet, the nozzle pressure ratios of 3–8 correspond to a range of pressure ratios from 0.383 to 1.022. Thus, these NPRs establish adverse and favorable pressure gradients at the nozzle exit. The results of this study show that the mixing promotion caused by tab at 0.75D is the best, resulting in a core length reduction of approximately 86% in the presence of a marginally favorable pressure gradient of 2.2%. Comparison of the present results with the corresponding results for uncorrugated limiting tabs available in literature show that the mixing promotion caused by the corrugated tab is superior to the tab without corrugation.
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Published In
Journal of Aerospace Engineering
Volume 31 • Issue 2 • March 2018
Copyright
©2017 American Society of Civil Engineers.
History
Received: Mar 31, 2017
Accepted: Aug 7, 2017
Published online: Nov 25, 2017
Published in print: Mar 1, 2018
Discussion open until: Apr 25, 2018
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