Airfoil Boundary-Layer Flow Control Using Fluidic Oscillators

Tenzin Choephel, James Coder, Mark D. Maughmer

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

10 Scopus citations

Abstract

Experiments were conducted to explore the use of fluidic oscillators for improving the aerodynamic performance of the S903 airfoil. The tests were conducted at chord Reynolds numbers ranging from 4 x 105 to 1 x 106 in the Low-Speed, Mid-Size Tunnel at the Pennsylvania State University. The improvement in lift coefficient range from 10% to 20% and depends on the Reynolds number and the actuation level. It was observed that the higher the oscillator jet velocity with respect to the free stream velocity, the higher the gain in aerodynamic performance at a given Reynolds number. It was also observed that the gain in maximum lift was nearly constant for varying Reynolds numbers if the ratio of jet velocity to the free stream velocity is kept constant. Numerical simulations were performed to study the effect of frequency of actuation for a given velocity ratio and to better understand the physics of the flow control mechanism involved.

Original languageEnglish (US)
Title of host publication30th AIAA Applied Aerodynamics Conference 2012
PublisherAmerican Institute of Aeronautics and Astronautics Inc.
Pages44-54
Number of pages11
ISBN (Print)9781624101854
DOIs
StatePublished - Jan 1 2012
Event30th AIAA Applied Aerodynamics Conference 2012 - New Orleans, LA, United States
Duration: Jun 25 2012Jun 28 2012

Publication series

Name30th AIAA Applied Aerodynamics Conference 2012

Other

Other30th AIAA Applied Aerodynamics Conference 2012
CountryUnited States
CityNew Orleans, LA
Period6/25/126/28/12

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering

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