A method for computation of the flow field around an arbitrary airfoil cascade on an axially symmetric blade-to-blade surface was developed which takes into account the development and separation of the blade surface boundary layers and mixing in the wake. The method predicts the overall fluid turning and total pressure loss in the context of an inviscid-viscous interaction scheme. The inviscid flow solution is obtained from a compressible flow matrix method. The viscous flow is obtained from a differential boundary layer method which calculates laminar, transitional and turbulent boundary layers. Provisions for the calculation of laminar and turbulent separation regions were added to the viscous scheme. The combined inviscid-viscous interaction scheme described yields results which are quantitatively consistent with experimental data. This suggests that the physical basis for the interactive system is correct and justifies continued exploration and use of the method.
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January 1980
This article was originally published in
Journal of Engineering for Power
Research Papers
Axial-Flow Compressor Turning Angle and Loss by Inviscid-Viscous Interaction Blade-to-Blade Computation
E. C. Hansen,
E. C. Hansen
Iowa State University, Ames, IA
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G. K. Serovy,
G. K. Serovy
Iowa State University, Ames, IA
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P. M. Sockol
P. M. Sockol
NASA-Lewis Research Center, Cleveland, OH
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E. C. Hansen
Iowa State University, Ames, IA
G. K. Serovy
Iowa State University, Ames, IA
P. M. Sockol
NASA-Lewis Research Center, Cleveland, OH
J. Eng. Power. Jan 1980, 102(1): 28-34 (7 pages)
Published Online: January 1, 1980
Article history
Received:
November 29, 1978
Online:
September 28, 2009
Citation
Hansen, E. C., Serovy, G. K., and Sockol, P. M. (January 1, 1980). "Axial-Flow Compressor Turning Angle and Loss by Inviscid-Viscous Interaction Blade-to-Blade Computation." ASME. J. Eng. Power. January 1980; 102(1): 28–34. https://doi.org/10.1115/1.3230228
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