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A Fast Method for the Prediction of Dynamic Stall Onset on Turbomachinery Blades PUBLIC ACCESS

[+] Author Affiliations
K. D. Jones, M. F. Platzer

Naval Postgraduate School, Monterey, CA

Paper No. 97-GT-101, pp. V004T14A017; 8 pages
doi:10.1115/97-GT-101
From:
  • ASME 1997 International Gas Turbine and Aeroengine Congress and Exhibition
  • Volume 4: Manufacturing Materials and Metallurgy; Ceramics; Structures and Dynamics; Controls, Diagnostics and Instrumentation; Education; IGTI Scholar Award
  • Orlando, Florida, USA, June 2–5, 1997
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7871-2
  • Copyright © 1997 by ASME

abstract

A computational approach is described for the rapid and systematic prediction and evaluation of the onset of dynamic stall due to rapid incidence changes or unsteady pitch or plunge motions. The method combines an unsteady, two-dimensional panel code with a two-dimensional boundary layer code. The panel code provides incompressible, inviscid flowfields about arbitrary airfoils undergoing prescribed motions. The boundary layer code computes laminar, transitional and turbulent regimes, with transition onset predicted by Michel’s criterion. Presented results demonstrate that the delay in dynamic stall onset is directly related to the dynamic pressure lag, in agreement with previous Navier-Stokes simulations, but in apparent disagreement with several aspects of the ‘moving wall’ analogy suggested in the past as an explanation for delayed dynamic stall onset.

Copyright © 1997 by ASME
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