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Power-on performance predictions for a complete generic hypersonic vehicle configuration

Author
Bennett, Bradford C.
Published
Apr 1, 1991.
Physical Description
1 electronic document
Online Version

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Unclassified, Unlimited, Publicly available.
Free-to-read Unrestricted online access
Summary
The Compressible Navier-Stokes (CNS) code was developed to compute external hypersonic flow fields. It has been applied to various hypersonic external flow applications. Here, the CNS code was modified to compute hypersonic internal flow fields. Calculations were performed on a Mach 18 sidewall compression inlet and on the Lewis Mach 5 inlet. The use of the ARC3D diagonal algorithm was evaluated for internal flows on the Mach 5 inlet flow. The initial modifications to the CNS code involved generalization of the boundary conditions and the addition of viscous terms in the second crossflow direction and modifications to the Baldwin-Lomax turbulence model for corner flows.
Other Subject(s)
Collection
NASA Technical Reports Server (NTRS) Collection.
Note
Document ID: 19910012766.
Accession ID: 91N22079.
MCAT-91-004.
NASA-CR-188152.
NAS 1.26:188152.
Terms of Use and Reproduction
No Copyright.
View MARC record | catkey: 15681484