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Path Optimization of Dual Airfoils Flapping in a Biplane Configuration with RSM in a Parallel Computing Environment

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Part of the Lecture Notes in Computational Science and Engineering book series (LNCSE,volume 74)

Abstract

The path of dual airfoils in a biplane configuration undergoing a combined, non–sinusoidal pitching and plunging motion is optimized for maximum thrust and/or propulsive efficiency. The non–sinusoidal, periodic flapping motion is described using Non-Uniform Rational B-Splines (NURBS). The Response Surface Methodology (RSM) is employed for the optimization of NURBS parameters in a parallel computing environment. A gradient based optimization algorithm, steepest ascent method is started from the optimum point of response surfaces. Unsteady, low speed laminar flows are also computed in parallel using a Navier-Stokes solver based on domain decomposition. It is shown that the parallel optimization process with RSM suggests a quick and accurate initial guess for a gradient based optimization algorithm.

Keywords

  • Response Surface Methodology
  • Path Optimization
  • Wall Clock Time
  • Steep Ascent
  • Maximum Thrust

These keywords were added by machine and not by the authors. This process is experimental and the keywords may be updated as the learning algorithm improves.

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Correspondence to Mustafa Kaya .

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Kaya, M., Tuncer, I.H. (2010). Path Optimization of Dual Airfoils Flapping in a Biplane Configuration with RSM in a Parallel Computing Environment. In: Tromeur-Dervout, D., Brenner, G., Emerson, D., Erhel, J. (eds) Parallel Computational Fluid Dynamics 2008. Lecture Notes in Computational Science and Engineering, vol 74. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-642-14438-7_8

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