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Aerodynamic shape optimization of supersonic aircraft configurations via an adjoint formulation on distributed memory parallel computers. (English) Zbl 0983.76077

From the summary: This work describes the application of a control theory-based aerodynamic shape optimization method to the problem of supersonic aircraft design. A high fidelity computational fluid dynamics algorithm modelling the Euler equations is used to calculate the aerodynamic properties of complex three-dimensional aircraft configurations. The design process is greatly accelerated through the use of both control theory and parallel computing. Control theory is employed to derive the adjoint differential equations whose solution allows for the evaluation of design gradient information at a fraction of the computational cost required by previous design methods. The resulting problem is then implemented in parallel using a domain decomposition approach, an optimized communication schedule, and the message passing interface standard for portability and efficiency.

MSC:

76N25 Flow control and optimization for compressible fluids and gas dynamics
76M30 Variational methods applied to problems in fluid mechanics
65Y05 Parallel numerical computation

Software:

MPI; NPSOL
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Full Text: DOI

References:

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