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An improved PNS scheme for predicting complex three-dimensional hypersonic flowsUpwinding is incorporated into a numerical technique for predicting hypersonic viscous flows over lifting configurations at moderate angles of attack. A general real-gas flux-vector-splitting technique based on Van Leer's (1982) approach is employed to model upwinding, and three techniques are examined for flux-vector differencing. The three methods are evaluated by applying them to an axisymmetric configuration with a 10-deg afterbody flare. The results indicate that an oscillation-free shock front can be described by using first-order full upwinding across the embedded shock and central-differencing for the other zones. This combined approach is found to be highly convergent for the near-wall region, and its performance is examined for predicting a Mach 15 flow over a finned missile. Attention is given to the effects of gas chemistry which can significantly affect the flows over the missile configurations.
Document ID
19920049055
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Bhutta, Bilal A.
(NASA Lewis Research Center Cleveland, OH, United States)
Lewis, Clark H.
(VRA, Inc. Blacksburg, VA, United States)
Date Acquired
August 15, 2013
Publication Date
January 1, 1992
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 92-0753
Accession Number
92A31679
Funding Number(s)
CONTRACT_GRANT: NAS3-25450
Distribution Limits
Public
Copyright
Other

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