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OPTIMAL DESIGN OF THE NACELLE ASSEMBLY UNDER THE WING OF AN AIRLINER BASED ON RANS NUMERICAL SIMULATIONS

Volumen 46, Edición 5, 2015, pp. 439-464
DOI: 10.1615/TsAGISciJ.v46.i5.30
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SINOPSIS

The key elements of the methodology of using the results of numerical simulations for the optimal aerodynamic design loop implemented in a basic propulsion system nacelle assembly under the wing of an airliner are considered. To illustrate the potentials of the considered methodology, the results of the optimization of the pylon geometry and spatial location of a high-bypass-ratio engine nacelle placed under the wing of a midrange airliner are presented.

CITADO POR
  1. Baranovski S. V., Mikhailovskiy K. V., The methods of designing an ultralight carbon fiber wing using parametrical modeling, XLIV ACADEMIC SPACE CONFERENCE: dedicated to the memory of academician S.P. Korolev and other outstanding Russian scientists – Pioneers of space exploration, 2318, 2021. Crossref

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