Essential Ingredients for the Computation of Steady and Unsteady Blade Boundary Layers

[+] Author and Article Information
H. M. Jang

Department of Mechanical Engineering, University of Michigan, Ann Arbor, MI 48109

J. A. Ekaterinaris

Navy-NASA Joint Institute of Aeronautics, Monterey, CA 93943

M. F. Platzer

Department of Aeronautics and Astronautics, Naval Postgraduate School, Monterey, CA 93943

T. Cebeci

Department of Aerospace Engineering, California State University, Long Beach, CA 90840

J. Turbomach 113(4), 608-616 (Oct 01, 1991) (9 pages) doi:10.1115/1.2929124 History: Received January 05, 1990; Online June 09, 2008


Two methods are described for calculating pressure distributions and boundary layers on blades subjected to low Reynolds numbers and ramp-type motion. The first is based on an interactive scheme in which the inviscid flow is computed by a panel method and the boundary layer flow by an inverse 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 with an embedded grid technique that permits accurate calculation of boundary layer flows. Studies for the Eppler-387 and NACA-0012 airfoils indicate that both methods can be used to calculate the behavior of unsteady blade boundary layers at low Reynolds numbers provided that the location of transition is computed with the en method and the transitional region is modeled properly.

Copyright © 1991 by The American Society of Mechanical Engineers
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