Radiative coupled viscous flow with massive blowing /
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Includes bibliographical references (p. 42-43).
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.
Prepared by Lockheed Missiles and Space Company, Sunnyvale, Calif. for Ames Research Center
- Chou, Y. S
- Contributing Institution
- University of Illinois
- Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service [distributor]
- Viscous flow--Mathematical models
Space vehicles--Atmospheric entry--Aerodynamics--Mathematical models
Radiative heat transfer
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- Public domain. Learn more at http://www.hathitrust.org/access_use
- Chicago citation style
- Chou, Y. S. Radiative coupled viscous flow with massive blowing /. 1973. Retrieved from the Digital Public Library of America, http://catalog.hathitrust.org/Record/011431452. (Accessed December 16, 2018.)
- APA citation style
- Chou, Y. S, (1973) Radiative coupled viscous flow with massive blowing /. Retrieved from the Digital Public Library of America, http://catalog.hathitrust.org/Record/011431452
- MLA citation style
- Chou, Y. S. Retrieved from the Digital Public Library of America <http://catalog.hathitrust.org/Record/011431452>.