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High Fidelity and High Performance Laminar Wing Optimization

"Proposed work aims at developing efficient optimization tools for NLF design where the cost function is the total drag (pressure and friction). The tool utilizes efficient and accurate computation of gradients of objective functi... ver más

30/06/2014

FOI

250K€

Presupuesto del proyecto: 250K€

Líder del proyecto

TOTALFORSVARETS FORSKNINGSINSTITUT No se ha especificado una descripción o un objeto social para esta compañía.

TRL 4-5

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Financiación concedida El organismo FP7 notifico la concesión del proyecto el día 2014-06-30 No tenemos la información de la convocatoria

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2 Participantes

FOI

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KTH

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Líder del proyecto

TOTALFORSVARETS FORSKNINGSINSTITUT No se ha especificado una descripción o un objeto social para esta compañía.

TRL 4-5

Presupuesto del proyecto 250K€

Fecha límite de participación Sin fecha límite de participación.

Descripción del proyecto "Proposed work aims at developing efficient optimization tools for NLF design where the cost function is the total drag (pressure and friction). The tool utilizes efficient and accurate computation of gradients of objective functions as well as robust parametrization of the geometry. Our approach uses Computational Fluid Dynamics followed by accurate boundary-layer stability analysis in order to find, by optimization, geometries that damp growth of boundary-layer disturbances in order to delay the laminar-turbulence transition. Gradient-based optimization and adjoint solvers are used in order to obtain the best numerical efficiency. The gradients are obtained through a chain of computations including adjoints of the flow equations and of the parabolized stability equations. Our method was initially developed for airfoils and recently extended to 3D wing design. Here, the tool will be improved by replacing the Euler equations of fluid dynamics by the Reynolds-Averaged Navier-Stokes (RANS) equations. This allows us to account for the viscous-inviscid interactions and therefore obtain a more accurate evaluation of the aerodynamic performances such as the total drag, lift and pitching moment. In order to ensure high accuracy of the gradients, the adjoint of the RANS solver will include adjoint of the turbulence model. A mesh-less method based on Radial Basis Functions will be used for deforming the RANS meshes. This approach has proven to be much faster than elliptic smoothers on meshes that are suitable for RANS computations. Here, two shape parametrization methods suitable for industrial design will be implemented and compared. Further, an automatic and efficient procedure for nonlocal stability analysis will be implemented in order to facilitate the use of this approach in industrial projects."

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