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Characteristic boundary conditions for three-dimensional transonic unsteady aerodynamicsCharacteristic far-field boundary conditions for the three-dimensional unsteady transonic small disturbance potential equation have been developed. The boundary conditions were implemented in the XTRAN3S finite difference code and tested for a flat plate rectangular wing with a pulse in angle of attack; the freestream Mach number was 0.85. The calculated force response shows that the characteristic boundary conditions reduce disturbances that are reflected from the computational boundaries.
Document ID
19850002607
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Whitlow, W., Jr. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 5, 2013
Publication Date
October 1, 1984
Subject Category
Aerodynamics
Report/Patent Number
NASA-TM-86292
NAS 1.15:86292
Accession Number
85N10915
Funding Number(s)
PROJECT: RTOP 505-33-43-09
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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