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Optimization of Duct Shape for Improving Aerodynamic Performance of Ducted Tail Rotor

Optimization of Duct Shape for Improving Aerodynamic Performance of Ducted Tail Rotor Numerical simulations on the aerodynamics of helicopter ducted tail rotor in hover are conducted, and a surrogate-based optimization framework is employed for the duct shape design in this work, by considering interactions between rotor and duct. The CFD analyses of ducted tail rotor are performed using the helicopter code CLORNS, including the momentum source method and high-fidelity CFD methods. The SA365N1 Dauphin fenestron in a test case is simulated by CFD methods and the duct shape is selected as baseline design for optimization. Parametric researches are conducted to investigate the relationship between the aerodynamic loads of ducted tail rotor and the variations of duct shape. Besides, the influence of duct shape on the flow details of rotor blade is obtained by resolving the flowfield based on high-fidelity CFD, and detailed analyses of the flow separation phenomenon downstream the rotor with large collective pitches are presented. Then, the multi-optimization of duct shape with different collective pitches is conducted by employing a surrogate-based optimization framework. Compared with the baseline design, the hovering efficiency of optimized design is improved because of a better negative pressure distribution on the duct wall. http://www.deepdyve.com/assets/images/DeepDyve-Logo-lg.png International Journal of Aeronautical and Space Sciences Springer Journals

Optimization of Duct Shape for Improving Aerodynamic Performance of Ducted Tail Rotor

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References (42)

Publisher
Springer Journals
Copyright
Copyright © The Author(s), under exclusive licence to The Korean Society for Aeronautical & Space Sciences 2022. Springer Nature or its licensor holds exclusive rights to this article under a publishing agreement with the author(s) or other rightsholder(s); author self-archiving of the accepted manuscript version of this article is solely governed by the terms of such publishing agreement and applicable law.
ISSN
2093-274X
eISSN
2093-2480
DOI
10.1007/s42405-022-00536-6
Publisher site
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Abstract

Numerical simulations on the aerodynamics of helicopter ducted tail rotor in hover are conducted, and a surrogate-based optimization framework is employed for the duct shape design in this work, by considering interactions between rotor and duct. The CFD analyses of ducted tail rotor are performed using the helicopter code CLORNS, including the momentum source method and high-fidelity CFD methods. The SA365N1 Dauphin fenestron in a test case is simulated by CFD methods and the duct shape is selected as baseline design for optimization. Parametric researches are conducted to investigate the relationship between the aerodynamic loads of ducted tail rotor and the variations of duct shape. Besides, the influence of duct shape on the flow details of rotor blade is obtained by resolving the flowfield based on high-fidelity CFD, and detailed analyses of the flow separation phenomenon downstream the rotor with large collective pitches are presented. Then, the multi-optimization of duct shape with different collective pitches is conducted by employing a surrogate-based optimization framework. Compared with the baseline design, the hovering efficiency of optimized design is improved because of a better negative pressure distribution on the duct wall.

Journal

International Journal of Aeronautical and Space Sciences – Springer Journals

Published: Apr 1, 2023

Keywords: Ducted tail rotor; Navier–Stokes equations; Momentum source method; Aerodynamic characteristics; Duct shape optimization

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