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An incremental strategy for calculating consistent discrete CFD sensitivity derivativesIn this preliminary study involving advanced computational fluid dynamic (CFD) codes, an incremental formulation, also known as the 'delta' or 'correction' form, is presented for solving the very large sparse systems of linear equations which are associated with aerodynamic sensitivity analysis. For typical problems in 2D, a direct solution method can be applied to these linear equations which are associated with aerodynamic sensitivity analysis. For typical problems in 2D, a direct solution method can be applied to these linear equations in either the standard or the incremental form, in which case the two are equivalent. Iterative methods appear to be needed for future 3D applications; however, because direct solver methods require much more computer memory than is currently available. Iterative methods for solving these equations in the standard form result in certain difficulties, such as ill-conditioning of the coefficient matrix, which can be overcome when these equations are cast in the incremental form; these and other benefits are discussed. The methodology is successfully implemented and tested in 2D using an upwind, cell-centered, finite volume formulation applied to the thin-layer Navier-Stokes equations. Results are presented for two laminar sample problems: (1) transonic flow through a double-throat nozzle; and (2) flow over an isolated airfoil.
Document ID
19920015438
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Korivi, Vamshi Mohan (NASA Langley Research Center Hampton, VA, United States)
Taylor, Arthur C., III (NASA Langley Research Center Hampton, VA, United States)
Newman, Perry A. (NASA Langley Research Center Hampton, VA, United States)
Hou, Gene W. (Old Dominion Univ. Norfolk, VA., United States)
Jones, Henry E. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 6, 2013
Publication Date
February 1, 1992
Subject Category
Aerodynamics
Report/Patent Number
NAS 1.15:104207
AVSCOM-TR-92-B-006
NASA-TM-104207
Report Number: NAS 1.15:104207
Report Number: AVSCOM-TR-92-B-006
Report Number: NASA-TM-104207
Accession Number
92N24681
Funding Number(s)
PROJECT: RTOP 505-59-53-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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