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Low-turbulence high-speed wind tunnel for the determination of cascade shock lossesA low turbulence high-speed wind tunnel, using anti-turbulence screening and a 100:1 contraction ratio, has been found suitable for high-speed smoke flow visualization. The location and strength of normal, oblique, and curved shock waves generated by transonic or supersonic wind tunnel flow over airfoils or through axial compressor cascades is determined by combined shadowgraph and smokelines visualization techniques without the interference effects caused by intrusive probes. The Reynolds number based on chord varied between 50,000 and 1,000,000. Preliminary results are compared with the relevant theory and data gathered using a total pressure probe.
Document ID
19790048385
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Slovisky, J. A. (Notre Dame, University Notre Dame, Ind., United States)
Roberts, W. B. (Nielsen Engineering and Research, Inc. Mountain View, Calif., United States)
Sandercock, D. M. (NASA Lewis Research Center Fan and Compressor Branch, Cleveland, Ohio, United States)
Date Acquired
August 9, 2013
Publication Date
March 1, 1979
Subject Category
Research And Support Facilities (Air)
Report/Patent Number
ASME PAPER 79-GT-129
Meeting Information
Meeting: American Society of Mechanical Engineers, Gas Turbine Conference and Exhibit and Solar Energy Conference
Location: San Diego, CA
Start Date: March 12, 1979
End Date: March 15, 1979
Sponsors: American Society of Mechanical Engineers
Accession Number
79A32398
Distribution Limits
Public
Copyright
Other

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