Numerical investigation of separation control for wing section at Re=300,000

A. Gross, H. F. Fasel

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

1 Scopus citations

Abstract

Active flow control by harmonic blowing through a slot is investigated for a modified NACA643-618 airfoil at a chord Reynolds number of Re=300,000 and for 15 degrees angle of attack. A direct simulation of the uncontrolled flow serves as a reference for hybrid simulations using a one-equation renormalization group turbulence model. Because of their lower computational expense, two-dimensional hybrid calculations are employed for active flow control parameter studies. Downstream harmonic blowing through a spanwise slot is investigated. For a blowing ratio of 0.1 the control is ineffective. For blowing ratios and dimensionless forcing frequencies between one and two the actuation results in vortex shedding of the separated boundary layer and a moderate rise in lift.

Original languageEnglish (US)
Title of host publication43rd Fluid Dynamics Conference
PublisherAmerican Institute of Aeronautics and Astronautics Inc.
ISBN (Print)9781624102141
DOIs
StatePublished - 2013
Event43rd AIAA Fluid Dynamics Conference - San Diego, CA, United States
Duration: Jun 24 2013Jun 27 2013

Publication series

Name43rd Fluid Dynamics Conference

Other

Other43rd AIAA Fluid Dynamics Conference
CountryUnited States
CitySan Diego, CA
Period6/24/136/27/13

ASJC Scopus subject areas

  • Fluid Flow and Transfer Processes
  • Energy Engineering and Power Technology
  • Aerospace Engineering
  • Mechanical Engineering

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    Gross, A., & Fasel, H. F. (2013). Numerical investigation of separation control for wing section at Re=300,000. In 43rd Fluid Dynamics Conference (43rd Fluid Dynamics Conference). American Institute of Aeronautics and Astronautics Inc.. https://doi.org/10.2514/6.2013-2751