Comparison of coupled radiative flow solutions with project fire II flight data

David R. Olynick, W. D. Henline, Lin H. Chambers, G. V. Candler

Research output: Contribution to journalArticlepeer-review

73 Scopus citations

Abstract

A nonequilibrium, axisymmetric, Navier-Stokes flow solver with coupled radiation has been developed for use in the design of thermal protection systems for vehicles where radiation effects are important. The present method has been compared with an existing flow and radiation solver and with the Project Fire II experimental data. Good agreement has been obtained over the entire Fire II trajectory with the experimentally determined values of the stagnation radiation intensity in the 0.2-6.2 eV range and with the total stagnation heating. The effects of a number of flow models are examined to determine which combination of physical models produces the best agreement with the experimental data. These models include radiation coupling, multitemperature thermal models, and finite rate chemistry. Finally, the computational efficiency of the present model is evaluated. The radiation properties model developed for this study is shown to offer significant computational savings compared to existing codes.

Original languageEnglish (US)
Pages (from-to)586-594
Number of pages9
JournalJournal of thermophysics and heat transfer
Volume9
Issue number4
DOIs
StatePublished - 1995

Bibliographical note

Funding Information:
The present research has been supported by a Grant from the National Research Council. Computer time has been provided by the Thermal Protection Materials Branch at NASA Ames Research Center. David Olynick would like to acknowledge some helpful suggestions from Tom Edwards.

Funding Information:
The present research has been supported by a Grant from the National Research Council. Computer time has been provided by the Thermal Protection Materials Branch at NASA Ames Research Center. David Olynick would like to ac- knowledge some helpful suggestions from Tom Edwards.

Publisher Copyright:
© 1994 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

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