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Aeroelastic Stability Analysis of Tailored Pretwisted Wings

Mohammadreza Amoozgar, S. Ahmad Fazelzadeh, Michael Friswell, Dewey H. Hodges

AIAA Journal, Volume: 57, Issue: 10, Pages: 4458 - 4466

Swansea University Authors: Mohammadreza Amoozgar, Michael Friswell

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DOI (Published version): 10.2514/1.j058575

Abstract

In this paper, the aeroelastic stability of a tailored aircraft wing with different pretwist distributions is investigated. The structure of the wing is modeled using the geometrically exact fully intrinsic beam theory of Hodges, whereas the aerodynamic loads are simulated by an incompressible unste...

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Published in: AIAA Journal
ISSN: 0001-1452 1533-385X
Published: American Institute of Aeronautics and Astronautics (AIAA) 2019
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URI: https://cronfa.swan.ac.uk/Record/cronfa53417
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fullrecord <?xml version="1.0"?><rfc1807><datestamp>2020-10-05T12:49:07.7092066</datestamp><bib-version>v2</bib-version><id>53417</id><entry>2020-02-03</entry><title>Aeroelastic Stability Analysis of Tailored Pretwisted Wings</title><swanseaauthors><author><sid>56910e9937b39a1a96d6252845c385d3</sid><firstname>Mohammadreza</firstname><surname>Amoozgar</surname><name>Mohammadreza Amoozgar</name><active>true</active><ethesisStudent>false</ethesisStudent></author><author><sid>5894777b8f9c6e64bde3568d68078d40</sid><firstname>Michael</firstname><surname>Friswell</surname><name>Michael Friswell</name><active>true</active><ethesisStudent>false</ethesisStudent></author></swanseaauthors><date>2020-02-03</date><deptcode>EEN</deptcode><abstract>In this paper, the aeroelastic stability of a tailored aircraft wing with different pretwist distributions is investigated. The structure of the wing is modeled using the geometrically exact fully intrinsic beam theory of Hodges, whereas the aerodynamic loads are simulated by an incompressible unsteady aerodynamic model. The governing nonlinear partial differential equations are discretized using a time-space scheme, and the stability of the system is sought by evaluating the eigenvalues of the linearized system. The wings have linear or quadratic pretwist distributions, and the effect of various twist angles on isotropic and tailored wings is investigated. In this study, the effect of pretwist is considered on both the aerodynamic and structural models. Moreover, the effect of wing structure taper ratio in conjunction with the pretwist is investigated. The preliminary results obtained for a wing modeled as a clamped-free beam are compared with those reported in the literature and excellent agreement is observed. It is concluded that the pretwist angle leads to mode coupling and also has a significant effect on the flutter speed of the wing. By pretwisting the wing, the flutter speed of the wing with respect to the clean wing increases until a specific twist value and then decreases. Moreover, adding the pretwist to the wing decreases the flutter frequency. Finally, results highlighting the effect of bend-twist elastic coupling and wing taper ratio in combination with the pretwist angle on the aeroelastic stability of the wing are provided.</abstract><type>Journal Article</type><journal>AIAA Journal</journal><volume>57</volume><journalNumber>10</journalNumber><paginationStart>4458</paginationStart><paginationEnd>4466</paginationEnd><publisher>American Institute of Aeronautics and Astronautics (AIAA)</publisher><issnPrint>0001-1452</issnPrint><issnElectronic>1533-385X</issnElectronic><keywords/><publishedDay>1</publishedDay><publishedMonth>10</publishedMonth><publishedYear>2019</publishedYear><publishedDate>2019-10-01</publishedDate><doi>10.2514/1.j058575</doi><url/><notes/><college>COLLEGE NANME</college><department>Engineering</department><CollegeCode>COLLEGE CODE</CollegeCode><DepartmentCode>EEN</DepartmentCode><institution>Swansea University</institution><apcterm/><lastEdited>2020-10-05T12:49:07.7092066</lastEdited><Created>2020-02-03T15:35:43.1253928</Created><path><level id="1">Faculty of Science and Engineering</level><level id="2">School of Engineering and Applied Sciences - Uncategorised</level></path><authors><author><firstname>Mohammadreza</firstname><surname>Amoozgar</surname><order>1</order></author><author><firstname>S. Ahmad</firstname><surname>Fazelzadeh</surname><order>2</order></author><author><firstname>Michael</firstname><surname>Friswell</surname><order>3</order></author><author><firstname>Dewey H.</firstname><surname>Hodges</surname><order>4</order></author></authors><documents/><OutputDurs/></rfc1807>
spelling 2020-10-05T12:49:07.7092066 v2 53417 2020-02-03 Aeroelastic Stability Analysis of Tailored Pretwisted Wings 56910e9937b39a1a96d6252845c385d3 Mohammadreza Amoozgar Mohammadreza Amoozgar true false 5894777b8f9c6e64bde3568d68078d40 Michael Friswell Michael Friswell true false 2020-02-03 EEN In this paper, the aeroelastic stability of a tailored aircraft wing with different pretwist distributions is investigated. The structure of the wing is modeled using the geometrically exact fully intrinsic beam theory of Hodges, whereas the aerodynamic loads are simulated by an incompressible unsteady aerodynamic model. The governing nonlinear partial differential equations are discretized using a time-space scheme, and the stability of the system is sought by evaluating the eigenvalues of the linearized system. The wings have linear or quadratic pretwist distributions, and the effect of various twist angles on isotropic and tailored wings is investigated. In this study, the effect of pretwist is considered on both the aerodynamic and structural models. Moreover, the effect of wing structure taper ratio in conjunction with the pretwist is investigated. The preliminary results obtained for a wing modeled as a clamped-free beam are compared with those reported in the literature and excellent agreement is observed. It is concluded that the pretwist angle leads to mode coupling and also has a significant effect on the flutter speed of the wing. By pretwisting the wing, the flutter speed of the wing with respect to the clean wing increases until a specific twist value and then decreases. Moreover, adding the pretwist to the wing decreases the flutter frequency. Finally, results highlighting the effect of bend-twist elastic coupling and wing taper ratio in combination with the pretwist angle on the aeroelastic stability of the wing are provided. Journal Article AIAA Journal 57 10 4458 4466 American Institute of Aeronautics and Astronautics (AIAA) 0001-1452 1533-385X 1 10 2019 2019-10-01 10.2514/1.j058575 COLLEGE NANME Engineering COLLEGE CODE EEN Swansea University 2020-10-05T12:49:07.7092066 2020-02-03T15:35:43.1253928 Faculty of Science and Engineering School of Engineering and Applied Sciences - Uncategorised Mohammadreza Amoozgar 1 S. Ahmad Fazelzadeh 2 Michael Friswell 3 Dewey H. Hodges 4
title Aeroelastic Stability Analysis of Tailored Pretwisted Wings
spellingShingle Aeroelastic Stability Analysis of Tailored Pretwisted Wings
Mohammadreza Amoozgar
Michael Friswell
title_short Aeroelastic Stability Analysis of Tailored Pretwisted Wings
title_full Aeroelastic Stability Analysis of Tailored Pretwisted Wings
title_fullStr Aeroelastic Stability Analysis of Tailored Pretwisted Wings
title_full_unstemmed Aeroelastic Stability Analysis of Tailored Pretwisted Wings
title_sort Aeroelastic Stability Analysis of Tailored Pretwisted Wings
author_id_str_mv 56910e9937b39a1a96d6252845c385d3
5894777b8f9c6e64bde3568d68078d40
author_id_fullname_str_mv 56910e9937b39a1a96d6252845c385d3_***_Mohammadreza Amoozgar
5894777b8f9c6e64bde3568d68078d40_***_Michael Friswell
author Mohammadreza Amoozgar
Michael Friswell
author2 Mohammadreza Amoozgar
S. Ahmad Fazelzadeh
Michael Friswell
Dewey H. Hodges
format Journal article
container_title AIAA Journal
container_volume 57
container_issue 10
container_start_page 4458
publishDate 2019
institution Swansea University
issn 0001-1452
1533-385X
doi_str_mv 10.2514/1.j058575
publisher American Institute of Aeronautics and Astronautics (AIAA)
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 Engineering and Applied Sciences - Uncategorised{{{_:::_}}}Faculty of Science and Engineering{{{_:::_}}}School of Engineering and Applied Sciences - Uncategorised
document_store_str 0
active_str 0
description In this paper, the aeroelastic stability of a tailored aircraft wing with different pretwist distributions is investigated. The structure of the wing is modeled using the geometrically exact fully intrinsic beam theory of Hodges, whereas the aerodynamic loads are simulated by an incompressible unsteady aerodynamic model. The governing nonlinear partial differential equations are discretized using a time-space scheme, and the stability of the system is sought by evaluating the eigenvalues of the linearized system. The wings have linear or quadratic pretwist distributions, and the effect of various twist angles on isotropic and tailored wings is investigated. In this study, the effect of pretwist is considered on both the aerodynamic and structural models. Moreover, the effect of wing structure taper ratio in conjunction with the pretwist is investigated. The preliminary results obtained for a wing modeled as a clamped-free beam are compared with those reported in the literature and excellent agreement is observed. It is concluded that the pretwist angle leads to mode coupling and also has a significant effect on the flutter speed of the wing. By pretwisting the wing, the flutter speed of the wing with respect to the clean wing increases until a specific twist value and then decreases. Moreover, adding the pretwist to the wing decreases the flutter frequency. Finally, results highlighting the effect of bend-twist elastic coupling and wing taper ratio in combination with the pretwist angle on the aeroelastic stability of the wing are provided.
published_date 2019-10-01T04:06:21Z
_version_ 1763753466651475968
score 11.012678

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