A New Circular Section Control for Streamwise Profiles in Aeroengine Nacelle Cowl Design and OptimizationSource: Journal of Aerospace Engineering:;2023:;Volume ( 036 ):;issue: 005::page 04023038-1DOI: 10.1061/JAEEEZ.ASENG-4758Publisher: ASCE
Abstract: Nacelle cowl design is dedicated to generating a three-dimensional surface with optimal drag performance. Most previous approaches focused primarily on the design method driven by streamwise profiles, which introduced no additional aerodynamically significant variables into the geometric constraints. Therefore, to explore more design spaces for drag reduction of the nacelle cowl, this paper proposes a design refinement method by adding a circular curve that passes through the locations of maximum thickness of given streamwise profiles at various angles toward the nacelle axis, which are regarded as the design variables. A proof-of-concept study was modeled using a combination of computer aided design, Latin hypercube sampling, computational fluid dynamics (CFD) simulation using Reynolds-averaged Navier–Stokes equations closed by a k-ω shear stress transport model, and a kriging surrogate model, in order to search for the optimal solution in design space. The result of optimization shows that the aerodynamic performance of the nacelle cowl was optimized significantly, with a 28.50% drag coefficient reduction with only three angular variables taken to create the design space, illustrating the feasibility of the proposed approach.
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contributor author | Zizhao Yuan | |
contributor author | Zhong Li | |
contributor author | Shuyue Wang | |
contributor author | Hao Zhang | |
contributor author | Gang Sun | |
contributor author | Yan Yan | |
contributor author | Bo Huang | |
date accessioned | 2023-11-27T23:04:54Z | |
date available | 2023-11-27T23:04:54Z | |
date issued | 5/27/2023 12:00:00 AM | |
date issued | 2023-05-27 | |
identifier other | JAEEEZ.ASENG-4758.pdf | |
identifier uri | http://yetl.yabesh.ir/yetl1/handle/yetl/4293270 | |
description abstract | Nacelle cowl design is dedicated to generating a three-dimensional surface with optimal drag performance. Most previous approaches focused primarily on the design method driven by streamwise profiles, which introduced no additional aerodynamically significant variables into the geometric constraints. Therefore, to explore more design spaces for drag reduction of the nacelle cowl, this paper proposes a design refinement method by adding a circular curve that passes through the locations of maximum thickness of given streamwise profiles at various angles toward the nacelle axis, which are regarded as the design variables. A proof-of-concept study was modeled using a combination of computer aided design, Latin hypercube sampling, computational fluid dynamics (CFD) simulation using Reynolds-averaged Navier–Stokes equations closed by a k-ω shear stress transport model, and a kriging surrogate model, in order to search for the optimal solution in design space. The result of optimization shows that the aerodynamic performance of the nacelle cowl was optimized significantly, with a 28.50% drag coefficient reduction with only three angular variables taken to create the design space, illustrating the feasibility of the proposed approach. | |
publisher | ASCE | |
title | A New Circular Section Control for Streamwise Profiles in Aeroengine Nacelle Cowl Design and Optimization | |
type | Journal Article | |
journal volume | 36 | |
journal issue | 5 | |
journal title | Journal of Aerospace Engineering | |
identifier doi | 10.1061/JAEEEZ.ASENG-4758 | |
journal fristpage | 04023038-1 | |
journal lastpage | 04023038-13 | |
page | 13 | |
tree | Journal of Aerospace Engineering:;2023:;Volume ( 036 ):;issue: 005 | |
contenttype | Fulltext |