Leading edge vortex separation study by different vortex and flow separation identification methods

Yangzi Huang, Melissa A. Green

Research output: Chapter in Book/Report/Conference proceedingConference contribution

1 Scopus citations

Abstract

The separation process of leading edge vortices (LEV) from an unsteady pitching plate is studied. The analysis processes a large amount of data from the two dimensional (2D) simulation of a at plate undergoing a 45° pitch-up maneuver. Large scale lift loss on the plate is shown to correlate with the vortex shedding. A Lagrangian coherent structures (LCS) analysis, including hyperbolic LCSs, Lagrangian-Averaged Vorticity Deviation (LAVD), and both FTLE saddle and λ-saddle are all applied around the LEV to identify the vortex dynamics. This is compared with a calculation of the circulation and the vortex shedding mechanism (VSM). The identified LEV dynamics revealed by multiple vortex criteria match with the circulation development and lift history in time, suggesting that LEV separation is a good model for various vortex shedding mechanisms.

Original languageEnglish (US)
Title of host publication8th AIAA Theoretical Fluid Mechanics Conference, 2017
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624104978
StatePublished - 2017
Externally publishedYes
Event8th AIAA Theoretical Fluid Mechanics Conference, 2017 - Denver, United States
Duration: Jun 5 2017Jun 9 2017

Publication series

Name8th AIAA Theoretical Fluid Mechanics Conference, 2017

Other

Other8th AIAA Theoretical Fluid Mechanics Conference, 2017
Country/TerritoryUnited States
CityDenver
Period6/5/176/9/17

Bibliographical note

Funding Information:
Dr. Jeff Eldredge and his research group at UCLA are gratefully acknowledged for sharing the database of simulation results for the current research. This work was supported by the Air Force Office of Scientific Research under AFOSR Award No. FA9550-14-1-0210.

Publisher Copyright:
© 2017, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.

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