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Contouring two-sided asymmetric plane maximum-thrust nozzles

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Abstract

The results of the optimal contouring of asymmetric plane nozzles under some additional constraints are presented. One of the constraints is due to the asymmetric arrangement of the unknown nozzles relative to the combustion chamber exit. The investigation is based on the numerical integration of the Reynolds-averaged Navier–Stokes equations and direct optimization methods using genetic algorithms and the representation of the optimized contours in the form of the Bernstein–Bézier curves.

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Authors and Affiliations

  1. Baranov Central Institute of Aviation Motors (CIAM), ul. Aviamotornaya 2, Moscow, 111116, Russia

    A. A. Kraiko, K. S. Pyankov & N. I. Tillyaeva

Authors
  1. A. A. Kraiko
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  2. K. S. Pyankov
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  3. N. I. Tillyaeva
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Correspondence to A. A. Kraiko.

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Original Russian Text © A.A. Kraiko, K.S. Pyankov, N.I. Tillyaeva, 2016, published in Izvestiya Rossiiskoi Akademii Nauk, Mekhanika Zhidkosti i Gaza, 2016, Vol. 51, No. 1, pp. 115–120.

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Kraiko, A.A., Pyankov, K.S. & Tillyaeva, N.I. Contouring two-sided asymmetric plane maximum-thrust nozzles. Fluid Dyn 51, 120–125 (2016). https://doi.org/10.1134/S0015462816010142

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