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Aerodynamic design modification of a hypersonic wind tunnel nozzle by CSCM with high order accuracyAn improved version of the CSCM implicit Navier-Stokes solver with a flexible data structure has been applied, in conjunction with a sophisticated patched grid system, to the aerodynamic analysis of hypersonic axisymmetric contoured nozzles of the NASA-Ames 3.5-foot hypersonic wind tunnel. The results obtained are found to be in good agreement with experiment. Based on the analysis, a newly designed throat contour for the Mach 14 nozzle has been recommended.
Document ID
19870058010
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Yang, J. Y. (PEDA Corp. Palo Alto, CA, United States)
Lombard, C. K. (PEDA Corp. Palo Alto, CA, United States)
Luh, R. C.-C. (PEDA Corp. Palo Alto, CA, United States)
Nagaraj, N. (PEDA Corp. Palo Alto, CA, United States)
Codding, W. H. (PEDA Corp. Palo Alto, CA, United States)
Date Acquired
August 13, 2013
Publication Date
June 1, 1987
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 87-1896
Accession Number
87A45284
Funding Number(s)
CONTRACT_GRANT: NAS2-12243
Distribution Limits
Public
Copyright
Other

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