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On an Efficient Method fo Time-Domain Computational Aeroelasticity
KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering.ORCID iD: 0000-0002-3199-8534
2005 (English)Doctoral thesis, comprehensive summary (Other scientific)
Abstract [en]

The present thesis summarizes work on developing a method for unsteady aerodynamic analysis primarily for aeroelastic simulations. In contrast to widely used prediction tools based on frequency-domain representations, the current approach aims to provide a time-domain simulation capability which can be readily integrated with possibly nonlinear structural and control system models. Further, due to the potential flow model underlying the computational method, and the solution algorithm based on an efficient boundary element formulation, the computational effort for the solution is moderate, allowing time-dependent simulations of complex configurations. The computational method is applied to simulate a number of wind-tunnel experiments involving highly flexible models. Two of the experiments are utilized to verify the method and to ascertain the validity of the unsteady flow model. In the third study, simulations are used for the numerical optimization of a configuration with multiple control surfaces. Here, the flexibility of the model is exploited in order to achieve a reduction of induced drag. Comparison with experimental results shows that the numerical method attains adequate accuracy within the inherent limits of the potential flow model. Finally, rather extensive aeroelastic simulations are performed for the ASK 21 sailplane. Time-domain simulations of a pull-up maneuver and comparisons with flight test data demonstrate that, considering modeling and computational effort, excellent agreement is obtained. Furthermore, a flutter analysis is performed for the same aircraft using identified frequency-domain loads. Results are found to deviate only slightly from critical speed and frequency obtained using an industry-standard aeroelastic analysis code. Nevertheless, erratic results for control surface hinge moments indicate that the accuracy of the present method would benefit from improved control surface modeling and coupled boundary layer analysis.

Place, publisher, year, edition, pages
Stockholm: KTH , 2005.
Series
Trita-AVE, ISSN 1651-7660 ; 2006:1
Keyword [en]
aeroelasticity, unsteady aerodynamics, boundary element method, multidisciplinary simulation
National Category
Vehicle Engineering
Identifiers
URN: urn:nbn:se:kth:diva-584ISBN: 91-7178-243-5 (print)OAI: oai:DiVA.org:kth-584DiVA: diva2:14501
Public defence
2006-01-24, Kollegiesalen F3, F, Lindstedtsvägen 26, Stockholm, 13:00 (English)
Opponent
Supervisors
Note
QC 20100531Available from: 2006-01-16 Created: 2006-01-16 Last updated: 2011-12-08Bibliographically approved
List of papers
1. An efficient method for time-domain low-speed aerodynamics: Theory and examples
Open this publication in new window or tab >>An efficient method for time-domain low-speed aerodynamics: Theory and examples
2005 (English)Report (Other academic)
Place, publisher, year, edition, pages
Stockholm: KTH, 2005
Series
Trita-AVE, ISSN 1651-7660 ; 2005:40
National Category
Engineering and Technology
Identifiers
urn:nbn:se:kth:diva-8975 (URN)
Note
QC 20100531Available from: 2006-01-16 Created: 2006-01-16 Last updated: 2010-05-31Bibliographically approved
2. An efficient aerodynamic boundary element method for aeroelastic simulations and its experimental validation
Open this publication in new window or tab >>An efficient aerodynamic boundary element method for aeroelastic simulations and its experimental validation
2003 (English)In: Aerospace Science & Technology, ISSN 1270-9638, Vol. 7, no 7, 532-539 p.Article in journal (Refereed) Published
National Category
Engineering and Technology
Identifiers
urn:nbn:se:kth:diva-8976 (URN)
Note
QC 20100531Available from: 2006-01-16 Created: 2006-01-16 Last updated: 2010-05-31Bibliographically approved
3. Approach to Induced Drag Reduction with Experimental Evaluation
Open this publication in new window or tab >>Approach to Induced Drag Reduction with Experimental Evaluation
2005 (English)In: Journal of Aircraft, ISSN 0021-8669, E-ISSN 1533-3868, Vol. 42, no 6, 1478-1485 p.Article in journal (Refereed) Published
Abstract [en]

An approach to minimize the induced drag of an aeroelastic configuration by means of multiple leading- and trailing-edge control surfaces is investigated. A computational model based on a boundary-element method is constructed and drag-reducing flap settings are found by means of numerical optimization. Further, experiments with an elastic wind-tunnel model are performed in order to evaluate the numerically obtained results. Induced-drag results are obtained by analyzing lift distributions computed from optically measured local angles of attack because standard techniques proved insufficient. Results show that significant reductions of induced drag of flexible wings can be achieved by using optimal control surface settings.

Keyword
Aeroelastic configuration; Drag reduction; Flap settings; Lift distributions
National Category
Engineering and Technology
Identifiers
urn:nbn:se:kth:diva-7268 (URN)10.2514/1.11713 (DOI)000233846200012 ()2-s2.0-29544442463 (Scopus ID)
Note
QC 20100531. Konferens: AIAA/ASME/ASCE/AHS/ASC 45th Structures, Structural Dynamics and Materials Conference Palm Springs, CA, APR 19-22, 2004Available from: 2007-06-01 Created: 2007-06-01 Last updated: 2017-12-14Bibliographically approved
4. Efficient flight mechanics simulation of elastic aircraft configurations
Open this publication in new window or tab >>Efficient flight mechanics simulation of elastic aircraft configurations
2005 (English)Conference paper, Published paper (Other academic)
National Category
Engineering and Technology
Identifiers
urn:nbn:se:kth:diva-8978 (URN)
Conference
International Forum for Aeroelasticity and Structural Dynamics
Note
QC 20100531Available from: 2006-01-16 Created: 2006-01-16 Last updated: 2010-05-31Bibliographically approved
5. Aeroelastic Simulations of a Sailplane
Open this publication in new window or tab >>Aeroelastic Simulations of a Sailplane
2005 (English)Report (Other academic)
Place, publisher, year, edition, pages
Stockholm: KTH, 2005
Series
Trita-AVE, ISSN 1651-7660 ; 2005:41
National Category
Engineering and Technology
Identifiers
urn:nbn:se:kth:diva-8979 (URN)
Note
QC 20100531Available from: 2006-01-16 Created: 2006-01-16 Last updated: 2010-05-31Bibliographically approved

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Eller, David

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