Get 20M+ Full-Text Papers For Less Than $1.50/day. Start a 14-Day Trial for You or Your Team.

Learn More →

Effect of Inlet Boundary Layer Suction on Flow Distortion in Subsonic Diffusing S-Duct

Effect of Inlet Boundary Layer Suction on Flow Distortion in Subsonic Diffusing S-Duct The effects of the boundary layer suction (BLS) near the S-duct inlet on the flow distortion of the S-duct were analyzed using a commercial computational fluid dynamics tool. The purpose of this study was to investigate the effect of shape factors on the location and length of the BLS for the RAE M 2129 S-duct with the inlet shape AR (0.75,0). The performance of the S-duct is influenced by the boundary layer thickness for duct flow and the counter-rotating vortex position on the engine face. All of the cases upon applying BLS were confirmed as having a different boundary layer thickness and the counter-rotating vortex at the engine face was confirmed. The PS (0,0.1) case has the thinnest boundary layer and the counter-rotating vortex is the farthest from the starboard side, while the PS (0.06,0.08) case has the thickest boundary layer and the counter-rotating vortex is located near the starboard side. In conclusion, it was confirmed that BLS has a significant influence on the flow distortion for the applied position compared to the applied length. Additionally, the PS (0,0.1) case applied near duct inlet showed the least flow distortion, and the PS (0.06,0.08) case located near the cowl lip showed the largest flow distortion. http://www.deepdyve.com/assets/images/DeepDyve-Logo-lg.png International Journal of Aeronautical & Space Sciences Springer Journals

Effect of Inlet Boundary Layer Suction on Flow Distortion in Subsonic Diffusing S-Duct

Download PDF
8 pages

Loading next page...
 
/lp/springer-journals/effect-of-inlet-boundary-layer-suction-on-flow-distortion-in-subsonic-izMav8gn0U

References (25)

Publisher
Springer Journals
Copyright
Copyright © 2019 by The Korean Society for Aeronautical & Space Sciences
Subject
Engineering; Aerospace Technology and Astronautics; Fluid- and Aerodynamics
ISSN
2093-274X
eISSN
2093-2480
DOI
10.1007/s42405-019-00175-4
Publisher site
See Article on Publisher Site

Abstract

The effects of the boundary layer suction (BLS) near the S-duct inlet on the flow distortion of the S-duct were analyzed using a commercial computational fluid dynamics tool. The purpose of this study was to investigate the effect of shape factors on the location and length of the BLS for the RAE M 2129 S-duct with the inlet shape AR (0.75,0). The performance of the S-duct is influenced by the boundary layer thickness for duct flow and the counter-rotating vortex position on the engine face. All of the cases upon applying BLS were confirmed as having a different boundary layer thickness and the counter-rotating vortex at the engine face was confirmed. The PS (0,0.1) case has the thinnest boundary layer and the counter-rotating vortex is the farthest from the starboard side, while the PS (0.06,0.08) case has the thickest boundary layer and the counter-rotating vortex is located near the starboard side. In conclusion, it was confirmed that BLS has a significant influence on the flow distortion for the applied position compared to the applied length. Additionally, the PS (0,0.1) case applied near duct inlet showed the least flow distortion, and the PS (0.06,0.08) case located near the cowl lip showed the largest flow distortion.

Journal

International Journal of Aeronautical & Space Sciences – Springer Journals

Published: May 24, 2019

There are no references for this article.