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

[+] Author Affiliations
H. M. Jang

University of Michigan, Ann Arbor, MI

M. F. Platzer

Naval Postgraduate School, Monterey, CA

J. A. Ekaterinaris

NASA Joint Inst. of Aeronautics

T. Cebeci

California State University, Long Beach, CA

Paper No. 90-GT-160, pp. V001T01A056; 11 pages
doi:10.1115/90-GT-160
From:
  • ASME 1990 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 1: Turbomachinery
  • Brussels, Belgium, June 11–14, 1990
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7904-7
  • Copyright © 1990 by ASME

abstract

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 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 modelled properly.

Copyright © 1990 by ASME
This article is only available in the PDF format.

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