Experimental and numerical investigation of corner stall in a highly-loaded compressor cascade

From National Research Council Canada

DOIResolve DOI: https://doi.org/10.1115/GT2014-27204
AuthorSearch for: 1; Search for: 2; Search for: 2
Name affiliation
  1. National Research Council of Canada. NRC Institute for Aerospace Research
  2. National Research Council of Canada. Aerospace
FormatText, Article
Proceedings titleProceedings of the ASME Turbo Expo
ConferenceASME Turbo Expo 2014: Turbine Technical Conference and Exposition, GT 2014, 16 June 2014 through 20 June 2014
SubjectAirfoils; Boundary layer flow; Compressors; Computational fluid dynamics; Inlet flow; Pressure gradient; Reynolds number; Turbulence; Wakes; Adverse pressure gradient; Compressor cascade; Compressor performance; Freestream turbulence intensity; Inlet boundary layer; Numerical investigations; Numerical predictions; Atmospheric thermodynamics
Publication date
PublisherAmerican Society of Mechanical Engineers
Peer reviewedYes
NPARC number21275531
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Record identifier7f83ca7e-9959-4377-94ab-6a55f694a149
Record created2015-07-14
Record modified2020-04-22
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