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Numerical simulation of unsteady flow in a hypersonic shock tunnel facilityThis paper describes the computational work performed on the simulation of a 16-in shock-tunnel facility. The numerical problems encountered during the computation of these flows are discussed along with the validity of some approximations used, notably concerning the reduction of the problem into problems of smaller dimensionality. Quasi-1D simulations can be used to help design experiments, or to better understanding the characteristics of the facility. An application to the design of a nonintrusive diagnostic is shown. The multidimensional flow transients computed include the shock reflection at the end of the driven tube, the shock propagation down the nozzle, and the breaking of the main diaphragm.
Document ID
19920074227
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Cambier, Jean-Luc
(Eloret Institute, Palo Alto; NASA, Ames Research Center Moffett Field, CA, United States)
Tokarcik, Susan
(NASA Ames Research Center Moffett Field, CA, United States)
Prabhu, Dinesh K.
(Eloret Institute Palo Alto, CA, United States)
Date Acquired
August 15, 2013
Publication Date
July 1, 1992
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 92-4029
Accession Number
92A56851
Distribution Limits
Public
Copyright
Other

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