C. Blondeau, T. Achard, P. Girodroux-Lavigne, R. Ohayon

DOI Number: N/A

Conference number: IFASD-2015-019

Strategies for developing and implementing discrete gradient methods for aeroelastic optimization for structured meshes are presented. For shape optimization of aerodynamic functions, discrete linear and adjoint techniques taking into account structural flexibility are introduced. To this end, all routines of the block-structured elsA/Aeroelastic solver have been systematically differentiated by hand. All operations are performed on-thefly for linear and tangent mode without any data storage or transposing thus leading to a very memory efficient implementation. These techniques are demonstrated on a flexible gradient computation exercise for the Onera M6 wing. Comparisons between rigid and flexible gradients are presented for Euler and Navier-stokes fluid. A second part of this paper presents a non-intrusive strategy for the computation of flexible gradients with respect to structural design parameters. To this end, a modal projection technique associated to a linearized frequency response solver is proposed. Alternatives to reduce the associated computational overhead are discussed. An illustration of this approach is presented for the M6 wing Euler test case.

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In Categories: 2. IFASD 2015, Aeroelastic Optimisation
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