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A shock-layer theory based on thirteen-moment equations and DSMC calculations of rarefied hypersonic flowsGrad's thirteen-moment equations are applied to the flow behind a bow shock under the formalism of a thin shock layer. Comparison of this version of the theory with Direct Simulation Monte Carlo calculations of flows about a flat plate at finite attack angle has lent support to the approach as a useful extension of the continuum model for studying translational nonequilibrium in the shock layer. This paper reassesses the physical basis and limitations of the development with additional calculations and comparisons. The streamline correlation principle, which allows transformation of the 13-moment based system to one based on the Navier-Stokes equations, is extended to a three-dimensional formulation. The development yields a strip theory for planar lifting surfaces at finite incidences. Examples reveal that the lift-to-drag ratio is little influenced by planform geometry and varies with altitudes according to a 'bridging function' determined by correlated two-dimensional calculations.
Document ID
19910036993
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Cheng, H. K.
(University of Southern California Los Angeles, CA, United States)
Wong, Eric Y.
(Southern California, University Los Angeles, CA, United States)
Dogra, V. K.
(Vigyan Research Associates, Inc Hampton, VA, United States)
Date Acquired
August 15, 2013
Publication Date
January 1, 1991
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 91-0783
Accession Number
91A21616
Funding Number(s)
CONTRACT_GRANT: NAGW-1061
Distribution Limits
Public
Copyright
Other

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