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    Investigations of the influence of the profile thickness of the compressible plane flow through compressor cascades (1978)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Flow-through cascade of an aircraft turbine compressor is studied experimentally over wide range of Reynolds numbers and subsonic Mach numbers; it was found that deterioration of flow properties due to decreasing Reynolds numbers is less noticeable on thin profiles than on thick ones; however, thick profiles are advantageous in compressors designed for efficient partial load behavior because thick profiles have a relatively large range of usable inlet flow angles.
    Keywords: AERODYNAMICS
    Type: NASA-TM-75277
    Format: application/pdf
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