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Sensitivity derivatives for advanced CFD algorithm and viscous modelling parameters via automatic differentiationThe computational technique of automatic differentiation (AD) is applied to a three-dimensional thin-layer Navier-Stokes multigrid flow solver to assess the feasibility and computational impact of obtaining exact sensitivity derivatives typical of those needed for sensitivity analyses. Calculations are performed for an ONERA M6 wing in transonic flow with both the Baldwin-Lomax and Johnson-King turbulence models. The wing lift, drag, and pitching moment coefficients are differentiated with respect to two different groups of input parameters. The first group consists of the second- and fourth-order damping coefficients of the computational algorithm, whereas the second group consists of two parameters in the viscous turbulent flow physics modelling. Results obtained via AD are compared, for both accuracy and computational efficiency with the results obtained with divided differences (DD). The AD results are accurate, extremely simple to obtain, and show significant computational advantage over those obtained by DD for some cases.
Document ID
19930057057
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Green, Lawrence L.
(NASA Langley Research Center Hampton, VA, United States)
Newman, Perry A.
(NASA Langley Research Center Hampton, VA, United States)
Haigler, Kara J.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 16, 2013
Publication Date
July 1, 1993
Subject Category
Computer Programming And Software
Report/Patent Number
AIAA PAPER 93-3321
Meeting Information
Meeting: AIAA, Computational Fluid Dynamics Conference
Location: Orlando, FL
Country: United States
Start Date: July 6, 1993
End Date: July 9, 1993
Sponsors: AIAA
Accession Number
93A41054
Distribution Limits
Public
Copyright
Other

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