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

DOIResolve DOI: http://doi.org/10.1115/GT2014-27204
AuthorSearch for: ; Search for: ; Search for:
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
AffiliationNational Research Council Canada (NRC-CNRC); NRC Institute for Aerospace Research; Aerospace
Peer reviewedYes
NPARC number21275531
Export citationExport as RIS
Report a correctionReport a correction
Record identifier7f83ca7e-9959-4377-94ab-6a55f694a149
Record created2015-07-14
Record modified2016-05-09
Bookmark and share
  • Share this page with Facebook (Opens in a new window)
  • Share this page with Twitter (Opens in a new window)
  • Share this page with Google+ (Opens in a new window)
Date modified: