Numerical Investigation of Unsteady Transitional Flow Over Oscillating Airfoil

[+] Author and Article Information
S.-W. Kim, K. B. M. Q. Zaman, J. Panda

NASA Lewis Research Center, Cleveland, OH 44135

J. Fluids Eng 117(1), 10-16 (Mar 01, 1995) (7 pages) doi:10.1115/1.2816799 History: Received August 06, 1993; Revised August 30, 1994; Online December 04, 2007


A numerical investigation of unsteady transitional flow over an oscillating NACA 0012 airfoil at a Reynolds number of 44,000 and reduced frequency of 0.2 is carried out and the results are compared with experimental data. The Navier-Stokes equations defined on arbitrary Lagrangian-Eulerian coordinates are solved by a time-accurate finite volume method that incorporates an incremental pressure equation for the conservation of mass. The transitional turbulence field is described by multiple-time-scale turbulence equations. The numerical method successfully predicts the large dynamic stall vortex (DSV) and the trailing edge vortex (TEV) that are periodically generated by the oscillating airfoil. The numerical results show that the transition from laminar to turbulent state and relaminarization occur widely in time and in space. The calculated streaklines and the ensemble-averaged velocity profiles are in good agreement with the measured data.

Copyright © 1995 by The American Society of Mechanical Engineers
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