A Fast Method for the Prediction of Dynamic Stall Onset on Turbomachinery Blades
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Authors
Jones, K.D.
Platzer, M.F.
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Date of Issue
1997
Date
1997
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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.
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Conference Paper
Description
ASME Paper No. 97-GT-101, presented at the 1997 ASME/IGTI Turbo Expo., Orlando, Florida, June 1997.
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Department of Mechanical and Aerospace Engineering
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Citation
Jones, K.D. and Platzer, M.F., "A Fast Method for the Prediction of Dynamic Stall Onset on Turbomachinery Blades," ASME Paper No. 97-GT-101, presented at the 1997 ASME/IGTI Turbo Expo., Orlando, Florida, June 1997.
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This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.