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Redesign and cascade tests of a supercritical controlled diffusion stator blade-sectionA supercritical stator blade section, previously tested in cascade, and characterized by a flat-roof-top suction surface Mach number distribution, has been redesigned and retested. At near design conditions, the losses and air turning were improved over the original blade by 50 percent and 7 percent, respectively. The key element in the improved performance was a small blade reshaping. This produced a continuous flow acceleration over the first one-third chord of the suction surface which successfully prevented a premature laminar separation bubble. Several recently available inviscid analysis codes and one fully viscous (Navier-Stokes) analysis code were used in the redesign process. The validity of these codes was enhanced by the test results. Previously announced in STAR as N84-22533
Document ID
19840054173
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Schmidt, J. F.
(NASA Lewis Research Center Cleveland, OH, United States)
Gelder, T. F.
(NASA Lewis Research Center Cleveland, OH, United States)
Donovan, L. F.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
August 12, 2013
Publication Date
June 1, 1984
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 84-1207
Accession Number
84A36960
Distribution Limits
Public
Copyright
Other

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