Item Details

Pitot-Probe Displacement in a Supersonic Turbulent Boundary Layer

Jerry M. Allen
Format
Book; Government Document; Online; EBook
Published
Washington, D.C. : National Aeronautics and Space Administration ; Springfield, VA : For sale by the Clearinghouse for Federal Scientific and Technical Information, 1972.
Language
English
Variant Title
NASA TN D-6759
Series
NASA Technical Note
Summary
Eight circular pitot probes ranging in size from 2 to 70 percent of the boundary-layer thickness were tested to provide experimental probe displacement results in a two-dimensional turbulent boundary layer at a nominal free-stream Mach number of 2 and unit Reynolds number of 8 million per meter. The displacement obtained in the study was larger than that reported by previous investigators in either an incompressible turbulent boundary layer or a supersonic laminar boundary layer. The large probes indicated distorted Mach number profiles, probably due to separation. When the probes were small enough to cause no appreciable distortion, the displacement was constant over most of the boundary layer. The displacement in the near-wall region decreased to negative displacement in some cases. This near-wall region was found to extend to about one probe diameter from the test surface.
Description
29 p. : ill. ; 27 cm.
Mode of access: Internet.
Notes
  • Prepared by Langley Research Center, Hampton, Va., 23365.
  • Includes bibliographical references (p. 13-14).
Series Statement
NASA technical note ; D-6759
Logo for Copyright Not EvaluatedCopyright Not Evaluated
Technical Details

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    a| NASA TN D-6759
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    a| Washington, D.C. : b| National Aeronautics and Space Administration ; a| Springfield, VA : b| For sale by the Clearinghouse for Federal Scientific and Technical Information, c| 1972.
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    a| 29 p. : b| ill. ; c| 27 cm.
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    a| NASA technical note ; v| D-6759
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    a| Prepared by Langley Research Center, Hampton, Va., 23365.
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    a| Includes bibliographical references (p. 13-14).
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    a| Eight circular pitot probes ranging in size from 2 to 70 percent of the boundary-layer thickness were tested to provide experimental probe displacement results in a two-dimensional turbulent boundary layer at a nominal free-stream Mach number of 2 and unit Reynolds number of 8 million per meter. The displacement obtained in the study was larger than that reported by previous investigators in either an incompressible turbulent boundary layer or a supersonic laminar boundary layer. The large probes indicated distorted Mach number profiles, probably due to separation. When the probes were small enough to cause no appreciable distortion, the displacement was constant over most of the boundary layer. The displacement in the near-wall region decreased to negative displacement in some cases. This near-wall region was found to extend to about one probe diameter from the test surface.
    538
      
      
    a| Mode of access: Internet.
    650
      
    0
    a| Aerodynamics, Supersonic.
    650
      
    0
    a| Pitot tubes.
    650
      
    0
    a| Turbulent boundary layer.
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    a| Langley Research Center.
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    a| United States. b| National Aeronautics and Space Administration.
    974
      
      
    b| UIU c| UIUC d| 20141113 s| google u| uiug.30112106884486 y| 1972 r| pd q| bib

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