Publication: Domain optimization of a multi-element airfoil using automatic differentiation
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Domain optimization of a multi-element airfoil using automatic differentiation

- Article in a journal -
 

Area
Computational Fluid Dynamics

Author(s)
T. Slawig

Published in
Advances in Engineering Software

Year
2000

Abstract
Automatic differentiation is used to study the dependence of drag and lift of a four-element airfoil with respect to the position of some flaps in Euler and turbulent Navier-Stokes flow. Aim is the optimization of a cost functional based on drag and lift with respect to the position of the flaps as design parameters. The position is defined by the angle of rotation of the flaps around fixed points. A smooth local grid transformation is presented which retains the neighborhood relations of the original unstructured mesh. The two-dimensional (2D) compressible Navier-Stokes/Euler solver NSC2KE from INRIA and a NAG quasi-Netwon optimization routine serve for the solution of the state equations and the optimization, respectively. The gradient information is supplied by the automatic differentiation tool ADIFOR by Argonne National Laboratory.

AD Tools
ADIFOR

BibTeX
@ARTICLE{
         Slawig2000Doo,
       title = "Domain optimization of a multi-element airfoil using automatic differentiation",
       journal = "Advances in Engineering Software",
       volume = "32",
       number = "3",
       pages = "225--237",
       year = "2000",
       issn = "0965-9978",
       doi = "DOI: 10.1016/S0965-9978(00)00087-9",
       url =
         "http://www.sciencedirect.com/science/article/B6V1P-42408GB-5/2/9c3ec2173b228ae1b86304ec09ecb7f6",
       author = "T. Slawig",
       keywords = "Domain optimization, Sensitivity analysis, Euler equations, Turbulent Navier-Stokes
         equations",
       abstract = "Automatic differentiation is used to study the dependence of drag and lift of a
         four-element airfoil with respect to the position of some flaps in Euler and turbulent Navier-Stokes
         flow. Aim is the optimization of a cost functional based on drag and lift with respect to the
         position of the flaps as design parameters. The position is defined by the angle of rotation of the
         flaps around fixed points. A smooth local grid transformation is presented which retains the
         neighborhood relations of the original unstructured mesh. The two-dimensional (2D) compressible
         Navier-Stokes/Euler solver NSC2KE from INRIA and a NAG quasi-Netwon optimization routine serve for
         the solution of the state equations and the optimization, respectively. The gradient information is
         supplied by the automatic differentiation tool Adifor by Argonne National Laboratory.",
       ad_area = "Computational Fluid Dynamics",
       ad_tools = "ADIFOR"
}


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