LES on turbulent separated flow around NACA0015 at reynolds number 1,600,000 toward active flow control

Kengo Asada, Makoto Sato, Taku Nonomura, Soshi Kawai, Hikaru Aono, Aiko Yakeno, Kozo Fujii

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

7 Citations (Scopus)

Abstract

Large-eddy simulation of a separated flow over NACA0015 at Reynolds number 1,600,000 at angle of attack 20.11 deg. is conducted to clarify the features of turbulent separated flow at high Reynolds number. The total number of grid point is approximately one billion, and a high order scheme is used in this computation. The LES result agrees with the experimental result in terms of the locations of the laminar-separation, turbulent reattachment, and the turbulent separation, and of the surface pressure distribution. The laminar-separation bubble is formed near the leading edge with turbulent transition. Then turbulent boundary layer develops over the airfoil surface and the flow is separated as a turbulent flow. The time-frequency analysis indicates there are two characteristic frequencies: 1)Strouhal number St = 100 at the turbulent reattachment point, 2)St = 4 at the turbulent separation point. These frequencies are expected as effective excitation frequencies to control the separated flow.

Original languageEnglish
Title of host publication32nd AIAA Applied Aerodynamics Conference
PublisherAmerican Institute of Aeronautics and Astronautics Inc.
ISBN (Print)9781624102882
DOIs
Publication statusPublished - 2014
Externally publishedYes
Event32nd AIAA Applied Aerodynamics Conference 2014 - Atlanta, GA, United States
Duration: 2014 Jun 162014 Jun 20

Publication series

Name32nd AIAA Applied Aerodynamics Conference

Other

Other32nd AIAA Applied Aerodynamics Conference 2014
Country/TerritoryUnited States
CityAtlanta, GA
Period14/6/1614/6/20

ASJC Scopus subject areas

  • Aerospace Engineering
  • Mechanical Engineering

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