Item Details

Radiative Coupled Viscous Flow With Massive Blowing

by Y.S. Chou
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 [distributor], 1973.
Language
English
Series
NASA Contractor Report
Summary
An analysis of the fully-coupled viscous, radiating flow past an ablating blunt body at hyperbolic entry conditions is presented. A detailed thermodynamics computation, as well as a realistic radiation transport model, is included. A locally nonsimilar approach is employed to solve the conservation equations away from the stagnation point. The validity of the locally nonsimilar approach is demonstrated for some nonablating cases. Sample calculations are made for the typical flight condition of a Jovian entry probe. The effects of the downstream injection of the ablation products of a carbon heat shield on the flux distribution around the body are discussed in detail. It is found that most of the radiative energy is absorbed by the injected carbon gas and dumped into the wake.
Description
vi, 43 p. : ill. ; 27 cm.
Mode of access: Internet.
Notes
  • "NASA CR-2236."
  • "March 1973."
  • Cover title.
  • Includes bibliographical references (p. 42-43).
Series Statement
NASA contractor report ; NASA CR-2236
Logo for No Copyright - United StatesNo Copyright - United States
Technical Details

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    a| TL521.3.C6 b| A3 no. 2236
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    a| Chou, Y. S.
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    1
    0
    a| Radiative coupled viscous flow with massive blowing / c| by Y.S. Chou.
    260
      
      
    a| Washington, D.C. : b| National Aeronautics and Space Administration ; a| Springfield, Va. : b| For sale by the National Technical Information Service [distributor], c| 1973.
    300
      
      
    a| vi, 43 p. : b| ill. ; c| 27 cm.
    490
      
    0
    a| NASA contractor report ; v| NASA CR-2236
    500
      
      
    a| "NASA CR-2236."
    500
      
      
    a| "March 1973."
    500
      
      
    a| Cover title.
    504
      
      
    a| Includes bibliographical references (p. 42-43).
    520
      
      
    a| An analysis of the fully-coupled viscous, radiating flow past an ablating blunt body at hyperbolic entry conditions is presented. A detailed thermodynamics computation, as well as a realistic radiation transport model, is included. A locally nonsimilar approach is employed to solve the conservation equations away from the stagnation point. The validity of the locally nonsimilar approach is demonstrated for some nonablating cases. Sample calculations are made for the typical flight condition of a Jovian entry probe. The effects of the downstream injection of the ablation products of a carbon heat shield on the flux distribution around the body are discussed in detail. It is found that most of the radiative energy is absorbed by the injected carbon gas and dumped into the wake.
    536
      
      
    a| Prepared by Lockheed Missiles and Space Company, Sunnyvale, Calif. for Ames Research Center b| NAS 2-6668
    538
      
      
    a| Mode of access: Internet.
    650
      
    0
    a| Viscous flow x| Mathematical models.
    650
      
    0
    a| Space vehicles x| Atmospheric entry x| Aerodynamics x| Mathematical models.
    650
      
    7
    a| Thermodynamics. 2| nasat
    650
      
    7
    a| Stagnation point. 2| nasat
    650
      
    7
    a| Radiative heat transfer. 2| nasat
    650
      
    7
    a| Planetary atmospheres. 2| nasat
    650
      
    7
    a| Jupiter probes. 2| nasat
    650
      
    7
    a| Boundary layers. 2| nasat
    650
      
    7
    a| Viscous flow. 2| nasat
    650
      
    7
    a| Hyperbolic reentry. 2| nasat
    650
      
    7
    a| Blunt bodies. 2| nasat
    650
      
    7
    a| Ablation. 2| nasat
    710
    2
      
    a| Ames Research Center.
    710
    2
      
    a| Lockheed Missiles and Space Company.
    974
      
      
    b| UIU c| UIUC d| 20141113 s| google u| uiug.30112106860791 y| 1973 r| pd q| bib

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