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Computation of unsteady flows over airfoilsTwo methods are described for calculating unsteady flows over rapidly pitching airfoils. The first method is based on an interactive scheme in which the inviscid flow is obtained by a panel method. The boundary layer flow is computed by an interactive method that makes use of the Hilbert integral to couple the solutions of the inviscid and viscous flow equations. The second method is based on the solution of the compressible Navier-Stokes equations. The solution of these equations is obtained with an approximately factorized numerical algorithm, and with single block or multiple grids which enable grid embedding to enhance the resolution at isolated flow regions. In addition, the attached flow region can be computed by the numerical solution of compressible boundary layer equations. Unsteady pressure distributions obtained with both methods are compared with available experimental data.
Document ID
Document Type
Conference Paper
Ekaterinaris, J. A. (Naval Postgraduate School Monterey, CA, United States)
Platzer, M. F. (Naval Postgraduate School Monterey, CA, United States)
Date Acquired
September 6, 2013
Publication Date
March 1, 1992
Publication Information
Publication: NASA. Ames Research Center, Physics of Forced Unsteady Separation
Subject Category
Distribution Limits
Work of the US Gov. Public Use Permitted.

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