Effective direct methods for aerodynamic shape optimization |
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Authors: | A A Kraiko K S P’yankov |
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Institution: | 1.Baranov Central Institute for Aircraft Engine Design (TsIAM),Moscow,Russia |
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Abstract: | A direct method for aerodynamic shape optimization based on the use of Bézier spline approximation is proposed. The method
is tested as applied to the optimization of the supersonic part of an axisymmetric de Laval nozzle. The optimization results
are compared with the exact solution obtained by the control contour method (variational nozzle) and with nozzles constructed
using another direct method, namely, local linearization. It is shown that both direct optimization methods can be used on
rather coarse grids without degrading the accuracy of the solution. The optimization procedure involves the isoperimetric
condition that the surface area of the nozzle is given and fixed, which prevents the use of the control contour method. Optimization
with allowance for viscosity is performed using the method. For fairly short maximum possible nozzle lengths in the range
of Reynolds numbers under consideration, it is shown that allowance for viscosity does not improve the nozzle shape produced
by optimization based on the Euler equations. The role of viscosity is reduced to the determination of an optimal length. |
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