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On an Exact Step Length in Gradient-Based Aerodynamic Shape Optimization—Part II: Viscous Flows

Farzad Mohebbi, Ben Evans Orcid Logo, Mathieu Sellier

Fluids, Volume: 6, Issue: 3, Start page: 106

Swansea University Authors: Farzad Mohebbi, Ben Evans Orcid Logo

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DOI (Published version): 10.3390/fluids6030106

Abstract

This study presents an extension of a previous study (On an Exact Step Length in Gradient-Based Aerodynamic Shape Optimization) to viscous transonic flows. In this work, we showed that the same procedure to derive an explicit expression for an exact step length in a gradient-based optimization metho...

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Published in: Fluids
ISSN: 2311-5521
Published: MDPI AG 2021
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URI: https://cronfa.swan.ac.uk/Record/cronfa56440
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first_indexed 2021-03-14T09:04:00Z
last_indexed 2023-01-11T14:35:40Z
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spelling 2022-10-31T18:48:37.4947492 v2 56440 2021-03-14 On an Exact Step Length in Gradient-Based Aerodynamic Shape Optimization—Part II: Viscous Flows 35d5780a36e2949d4a6b6268c3dc1db0 Farzad Mohebbi Farzad Mohebbi true false 3d273fecc8121fe6b53b8fe5281b9c97 0000-0003-3662-9583 Ben Evans Ben Evans true false 2021-03-14 AERO This study presents an extension of a previous study (On an Exact Step Length in Gradient-Based Aerodynamic Shape Optimization) to viscous transonic flows. In this work, we showed that the same procedure to derive an explicit expression for an exact step length in a gradient-based optimization method for inviscid transonic flows can be employed for viscous transonic flows. The extended numerical method was evaluated for the viscous flows over the transonic RAE 2822 airfoil at two common flow conditions in the transonic regime. To do so, the RAE 2822 airfoil was reconstructed by a Bezier curve of degree 16. The numerical solution of the transonic turbulent flow over the airfoil was performed using the solver ANSYS Fluent (using the Spalart–Allmaras turbulence model). Using the proposed step length, a gradient-based optimization method was employed to minimize the drag-to-lift ratio of the airfoil. The gradient of the objective function with respect to design variables was calculated by the finite-difference method. Efficiency and accuracy of the proposed method were investigated through two test cases. Journal Article Fluids 6 3 106 MDPI AG 2311-5521 step length; Bezier curve; aerodynamic shape optimization; viscous flows; finite-difference method 4 3 2021 2021-03-04 10.3390/fluids6030106 COLLEGE NANME Aerospace Engineering COLLEGE CODE AERO Swansea University 2022-10-31T18:48:37.4947492 2021-03-14T08:58:34.4785687 Faculty of Science and Engineering School of Aerospace, Civil, Electrical, General and Mechanical Engineering - Aerospace Engineering Farzad Mohebbi 1 Ben Evans 0000-0003-3662-9583 2 Mathieu Sellier 3 56440__19531__24068e4d2e3846928190bb9c8b9c97af.pdf 56440.pdf 2021-03-23T12:41:10.4070930 Output 3748661 application/pdf Version of Record true Copyright: © 2021 by the authors. This article is an open access article distributed under the terms of the Creative Commons Attribution (CC BY) license true eng https://creativecommons.org/licenses/by/4.0/
title On an Exact Step Length in Gradient-Based Aerodynamic Shape Optimization—Part II: Viscous Flows
spellingShingle On an Exact Step Length in Gradient-Based Aerodynamic Shape Optimization—Part II: Viscous Flows
Farzad Mohebbi
Ben Evans
title_short On an Exact Step Length in Gradient-Based Aerodynamic Shape Optimization—Part II: Viscous Flows
title_full On an Exact Step Length in Gradient-Based Aerodynamic Shape Optimization—Part II: Viscous Flows
title_fullStr On an Exact Step Length in Gradient-Based Aerodynamic Shape Optimization—Part II: Viscous Flows
title_full_unstemmed On an Exact Step Length in Gradient-Based Aerodynamic Shape Optimization—Part II: Viscous Flows
title_sort On an Exact Step Length in Gradient-Based Aerodynamic Shape Optimization—Part II: Viscous Flows
author_id_str_mv 35d5780a36e2949d4a6b6268c3dc1db0
3d273fecc8121fe6b53b8fe5281b9c97
author_id_fullname_str_mv 35d5780a36e2949d4a6b6268c3dc1db0_***_Farzad Mohebbi
3d273fecc8121fe6b53b8fe5281b9c97_***_Ben Evans
author Farzad Mohebbi
Ben Evans
author2 Farzad Mohebbi
Ben Evans
Mathieu Sellier
format Journal article
container_title Fluids
container_volume 6
container_issue 3
container_start_page 106
publishDate 2021
institution Swansea University
issn 2311-5521
doi_str_mv 10.3390/fluids6030106
publisher MDPI AG
college_str Faculty of Science and Engineering
hierarchytype
hierarchy_top_id facultyofscienceandengineering
hierarchy_top_title Faculty of Science and Engineering
hierarchy_parent_id facultyofscienceandengineering
hierarchy_parent_title Faculty of Science and Engineering
department_str School of Aerospace, Civil, Electrical, General and Mechanical Engineering - Aerospace Engineering{{{_:::_}}}Faculty of Science and Engineering{{{_:::_}}}School of Aerospace, Civil, Electrical, General and Mechanical Engineering - Aerospace Engineering
document_store_str 1
active_str 0
description This study presents an extension of a previous study (On an Exact Step Length in Gradient-Based Aerodynamic Shape Optimization) to viscous transonic flows. In this work, we showed that the same procedure to derive an explicit expression for an exact step length in a gradient-based optimization method for inviscid transonic flows can be employed for viscous transonic flows. The extended numerical method was evaluated for the viscous flows over the transonic RAE 2822 airfoil at two common flow conditions in the transonic regime. To do so, the RAE 2822 airfoil was reconstructed by a Bezier curve of degree 16. The numerical solution of the transonic turbulent flow over the airfoil was performed using the solver ANSYS Fluent (using the Spalart–Allmaras turbulence model). Using the proposed step length, a gradient-based optimization method was employed to minimize the drag-to-lift ratio of the airfoil. The gradient of the objective function with respect to design variables was calculated by the finite-difference method. Efficiency and accuracy of the proposed method were investigated through two test cases.
published_date 2021-03-04T04:11:24Z
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score 11.016235

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