Numerical investigation of separation control for wing sections

A. Gross, H. F. Fasel

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

4 Scopus citations


Numerical simulations of the unsteady separated flow over wing sections at flight Reynolds numbers are challenging. Direct numerical simulations which resolve all scales of the fluid motion promise the highest degree of fidelity but are computationally very expensive. Even large-eddy simulations can be prohibitively expensive because of the high grid resolution required near the walls. Hybrid turbulence models employ Reynolds-averaged Navier-Stokes near the walls and adjust the turbulence model contribution away from the walls according to the local physical grid resolution. In this paper hybrid simulations based on a one-equation renormalization group model are presented for a modified NACA643-618 airfoil at a chord Reynolds number of 1 million and for 10, 20, and 30 degrees angle of attack. For these conditions a short laminar separation bubble develops near the leading edge and the flow separates turbulent from the suction side downstream of the leading edge bubble. For 10 degrees angle of attack the lift and drag data obtained from the simulations are in good agreement with XFoil predictions and active flow control by harmonic blowing through a spanwise slot upstream of the turbulent separation is investigated.

Original languageEnglish (US)
Title of host publication6th AIAA Flow Control Conference 2012
PublisherAmerican Institute of Aeronautics and Astronautics Inc.
ISBN (Print)9781624101885
StatePublished - 2012
Event6th AIAA Flow Control Conference 2012 - New Orleans, LA, United States
Duration: Jun 25 2012Jun 28 2012

Publication series

Name6th AIAA Flow Control Conference 2012


Other6th AIAA Flow Control Conference 2012
Country/TerritoryUnited States
CityNew Orleans, LA

ASJC Scopus subject areas

  • Fluid Flow and Transfer Processes
  • Aerospace Engineering
  • Control and Systems Engineering


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