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

From National Research Council Canada

DOIResolve DOI: http://doi.org/10.1115/GT2014-27204
AuthorSearch for: 1 ; Search for: 2 ; Search for: 2 
Name affiliation
  1. National Research Council Canada. NRC Institute for Aerospace Research
  2. National Research Council Canada. Aerospace
TypeArticle
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
ISBN9780791845608
Volume2A
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
Abstract
Publication date
PublisherAmerican Society of Mechanical Engineers
LanguageEnglish
Peer reviewedYes
NPARC number21275531
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Record created2015-07-14
Record modified2016-05-09
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