Examination of the leading edge flow structure of a dynamically pitching NACA 0012 airfoil Conference Paper uri icon


  • The purpose of this paper is to examine the leading-edge flow structure during dynamics stall under realistic helicopter flight conditions (M = 0.2 and Rec = 2 106). The test article was a rectangular wing with a NACA 0012 airfoil section. The wing was dynamically pitched about the 1/4 -chord at a reduced frequency of 0.1. The leading-edge flow structure was quantified experimentally using high-fidelity PIV (measurement resolution of 0.25 mm 0.25 mm). Numerical simulations were performed using a variety of turbulence models. The experimental and numerical data were analyzed to provide better understanding of the leading-edge flow dynamics. Improved understanding of the leading-edge flow dynamics has the potential to provide the scientific background necessary to identify new flow control opportunities. Copyright 2009 by the American Institute of Aeronautics and Astronautics, Inc.

published proceedings

  • 47th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition

author list (cited authors)

  • Sahoo, D., Srinivasan, R., & Bowersox, R.

complete list of authors

  • Sahoo, D||Srinivasan, R||Bowersox, RDW

publication date

  • December 2009