Solution of plane cascade flow using improved surface singularity methodsA solution method has been developed for calculating compressible inviscid flow through a linear cascade of arbitrary blade shapes. The method uses advanced surface singularity formulations which were adapted from those found in current external flow analyses. The resulting solution technique provides a fast flexible calculation for flows through turbomachinery blade rows. The solution method and some examples of the method's capabilities are presented.
Document ID
19810045664
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Mcfarland, E. R. (NASA Lewis Research Center Cleveland, Ohio, United States)
Date Acquired
August 11, 2013
Publication Date
March 1, 1981
Subject Category
Aerodynamics
Report/Patent Number
ASME PAPER 81-GT-169
Meeting Information
Meeting: Gas Turbine Conference and Products Show
Location: Houston, TX
Start Date: March 9, 1981
End Date: March 12, 1981
Sponsors: American Society of Mechanical Engineers