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 Canada. NRC Institute for Aerospace Research
  2. National Research Council Canada. Aerospace
FormatText
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
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LanguageEnglish
Peer reviewedYes
NPARC number21275531
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Record identifier7f83ca7e-9959-4377-94ab-6a55f694a149
Record created2015-07-14
Record modified2016-05-09
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