Abstract
A numerical method has been developed to predict the three-dimensional nonequilibrium flowfield past the Space Shuttle Orbiter at high angle of attack. An existing viscous shock-layer method has been extended to include finite-rate chemical reactions of multicomponen t ionizing air. A general nonorthogonal computational grid system was introduced to treat the nonaxisymmetric geometry. At Shuttle re-entry flight conditions, nonequilibrium real gas effects on the surface-measurable quantities are significant. The present method can predict the nonequilibrium flowfield over the entire windward surface of the Shuttle Orbiter at high angle of attack (up to 50 deg). The computational results obtained show good agreement compared to the STS-2 flight data and other numerical solutions.
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