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
  1. National Research Council of Canada. NRC Institute for Aerospace Research
  2. National Research Council of Canada. Aerospace
FormatText, Article
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
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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