Item Details

Analytical and Experimental Studies of Shock Interference Heating in Hypersonic Flows

by J. Wayne Keyes and Frank D. Hains
Format
Book; Government Document; Online; EBook
Published
Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1973.
Language
English
Series
NASA Technical Note
Summary
An analytical and experimental study is presented of the aerodynamic heating resulting from six types of shock interference patterns encountered in high speed flow. Centerline measurements of pressure and heat transfer distributions on basic bodies were obtained in four wind tunnels for Mach numbers from 6 to 20, specific heat ratios from 1.27 to 1.67, and free stream Reynolds numbers from 3 million to 25.6 million per meter. Peak heating and peak pressures up to 17 and 7.5 times stagnation values, respectively, were measured. In general, results obtained from semiempirical methods developed for each of the six types of interference agreed with the experimental peaks.
Description
iv, 137 p. : ill. ; 27 cm.
Mode of access: Internet.
Notes
  • Research prepared at Langley Research Center.
  • Cover title.
  • Bibliography: p. 34-39.
Series Statement
NASA technical note ; NASA TN D-7139
Logo for Copyright Not EvaluatedCopyright Not Evaluated
Technical Details

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    a| Analytical and experimental studies of shock interference heating in hypersonic flows c| by J. Wayne Keyes and Frank D. Hains.
    260
      
      
    a| Washington, D.C. : b| National Aeronautics and Space Administration ; a| [Springfield, Va. : b| For sale by the National Technical Information Service], c| 1973.
    300
      
      
    a| iv, 137 p. : b| ill. ; c| 27 cm.
    490
    0
      
    a| NASA technical note ; v| NASA TN D-7139
    500
      
      
    a| Research prepared at Langley Research Center.
    500
      
      
    a| Cover title.
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    a| Bibliography: p. 34-39.
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    a| An analytical and experimental study is presented of the aerodynamic heating resulting from six types of shock interference patterns encountered in high speed flow. Centerline measurements of pressure and heat transfer distributions on basic bodies were obtained in four wind tunnels for Mach numbers from 6 to 20, specific heat ratios from 1.27 to 1.67, and free stream Reynolds numbers from 3 million to 25.6 million per meter. Peak heating and peak pressures up to 17 and 7.5 times stagnation values, respectively, were measured. In general, results obtained from semiempirical methods developed for each of the six types of interference agreed with the experimental peaks.
    538
      
      
    a| Mode of access: Internet.
    650
      
    0
    a| Shock waves.
    650
      
    0
    a| Boundary layer.
    650
      
    0
    a| Aerodynamics, Hypersonic.
    650
      
    0
    a| Aerodynamic heating.
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    1
      
    a| Hains, Frank D.
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    1
      
    a| United States. b| National Aeronautics and Space Administration.
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    a| Langley Research Center.
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    b| UIU c| UIUC d| 20141113 s| google u| uiug.30112106885186 y| 1973 r| pd q| bib

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