Item Details

A Study of the Effects of Reynolds Number and Mach Number on Constant Pressure Coefficient Jump for Shock-Induced Trailing-Edge Separation

Atlee M. Cunningham, Jr., and Gregory S. Spragle
Format
Book; Government Document; Online; EBook
Published
Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va. : For sale by the National Technical Information Service, 1987.
Language
English
Series
NASA Contractor Report
Description
79 p. : ill. ; 28 cm.
Mode of access: Internet.
Notes
  • "August 1987"--Cover.
  • "Prepared for Langley Research Center under Contract NAS1-17955."
  • Includes bibliographical references (p. 28-31).
Series Statement
NASA contractor report ; 4090
Logo for No Copyright - United StatesNo Copyright - United States
Technical Details

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    a| A study of the effects of Reynolds number and mach number on constant pressure coefficient jump for shock-induced trailing-edge separation / c| Atlee M. Cunningham, Jr., and Gregory S. Spragle.
    260
      
      
    a| Washington, D.C. : b| National Aeronautics and Space Administration, Scientific and Technical Information Office ; a| Springfield, Va. : b| For sale by the National Technical Information Service, c| 1987.
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    a| 79 p. : b| ill. ; c| 28 cm.
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    a| NASA contractor report ; v| 4090
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    a| "August 1987"--Cover.
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    a| "Prepared for Langley Research Center under Contract NAS1-17955."
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    a| Includes bibliographical references (p. 28-31).
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    a| Mode of access: Internet.
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    a| Boundary layer.
    650
      
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    a| Shock waves.
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    a| Mach number.
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    a| Reynolds number.
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    a| Aerodynamics, Transonic.
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    b| UIU c| UIUC d| 20141113 s| google u| uiug.30112106862243 y| 1987 r| pd q| bib

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