DES of a Slingsby Firefly Aircraft: Unsteady Flow Feature Extraction Using POD and HODMD

Adrián Corrochano; Ana F. Neves; Bidur Khanal; Soledad Le Clainche; Nicholas J. Lawson

doi:10.1061/(asce)as.1943-5525.0001457

DES of a Slingsby Firefly Aircraft: Unsteady Flow Feature Extraction Using POD and HODMD

Adrián Corrochano, Ana F. Neves, Bidur Khanal, Soledad Le Clainche, Nicholas J. Lawson

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Abstract

In this paper, higher-order dynamic mode decomposition (HODMD) was applied to find the main patterns and frequencies of a transient aerodynamic flow field when an aircraft wing experiences stall. This method was applied to a computational flow simulation with a turbulence model based on a hybrid Reynolds-averaged Navier-Stokes large-eddy simulation (RANS/LES) [commonly known as detached-eddy simulation (DES)], where a combination of two-dimensional (2D) and three-dimensional (3D) flow visualization techniques are used to understand the vortex shedding from the main wing and its interaction with the tailplane. Simulation results were compared to the experimental ones and the results with proper orthogonal decomposition (POD) were compared with the HODMD analysis. The main advantage of HODMD resides in its identification of the main physical phenomena and the most relevant instabilities that lead the fluid dynamics. New flow control strategies can be defined when the underlying physics and the flow dynamics are known. Moreover, HODMD is robust in noisy and turbulent databases using less data than fast Fourier transform (FFT), which gives potential for future flow control applications, focused on improving the aircraft’s efficiency

Original language	English
Journal	Journal of Aerospace Engineering
Volume	35
Issue number	5
Early online date	2 Jun 2022
DOIs	https://doi.org/10.1061/(asce)as.1943-5525.0001457
Publication status	Published - 1 Sept 2022

Bibliographical note

Copyright © and Moral Rights are retained by the author(s) and/ or other copyright owners. A copy can be downloaded for personal non-commercial research or study, without prior permission or charge. This item cannot be reproduced or quoted extensively from without first obtaining permission in writing from the copyright holder(s). The content must not be changed in any way or sold commercially in any format or medium without the formal permission of the copyright holders.

This document is the author’s post-print version, incorporating any revisions agreed during the peer-review process. Some differences between the published version and this version may remain and you are advised to consult the published version if you wish to cite from it.

Funder

A. C. and S. L. C. acknowledge the Grant PID2020-114173RB-I00 funded by MCIN/AEI/ 10.13039/501100011033. A. C. acknowledges the support of Universidad Politécnica de Madrid, under the program Programa Propio.

Keywords

Mechanical Engineering
Aerospace Engineering
General Materials Science
Civil and Structural Engineering

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10.1061/(asce)as.1943-5525.0001457

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Cite this

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abstract = "In this paper, higher-order dynamic mode decomposition (HODMD) was applied to find the main patterns and frequencies of a transient aerodynamic flow field when an aircraft wing experiences stall. This method was applied to a computational flow simulation with a turbulence model based on a hybrid Reynolds-averaged Navier-Stokes large-eddy simulation (RANS/LES) [commonly known as detached-eddy simulation (DES)], where a combination of two-dimensional (2D) and three-dimensional (3D) flow visualization techniques are used to understand the vortex shedding from the main wing and its interaction with the tailplane. Simulation results were compared to the experimental ones and the results with proper orthogonal decomposition (POD) were compared with the HODMD analysis. The main advantage of HODMD resides in its identification of the main physical phenomena and the most relevant instabilities that lead the fluid dynamics. New flow control strategies can be defined when the underlying physics and the flow dynamics are known. Moreover, HODMD is robust in noisy and turbulent databases using less data than fast Fourier transform (FFT), which gives potential for future flow control applications, focused on improving the aircraft{\textquoteright}s efficiency",

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DES of a Slingsby Firefly Aircraft: Unsteady Flow Feature Extraction Using POD and HODMD

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