Delft Parametric Flutter Margin (PFM) Test Data Archive

doi: 10.4121/21656672.v1
The doi above is for this specific version of this dataset, which is currently the latest. Newer versions may be published in the future. For a link that will always point to the latest version, please use
doi: 10.4121/21656672
Datacite citation style:
de Boer, Stefan; Karpel, Moti; Sodja, Jurij (2023): Delft Parametric Flutter Margin (PFM) Test Data Archive. Version 1. 4TU.ResearchData. dataset. https://doi.org/10.4121/21656672.v1
Other citation styles (APA, Harvard, MLA, Vancouver, Chicago, IEEE) available at Datacite
Dataset
Delft University of Technology logo
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geolocation
Open Jet Facility, TU Delft
licence
cc-by.png logo CC BY 4.0

The dataset corresponds to the supplementary data for the paper titled 'Safe Flutter Determination for Wings Undergoing Large Deflections' (link: https://arc.aiaa.org/eprint/HDIFICQ9BW3BMFT2ZAAM/full/10.2514/6.2023-0379) and the MSc thesis entitled 'Safe Flutter Determination for Wings Undergoing Large Deflections' (link: http://resolver.tudelft.nl/uuid:b0e12214-ca2a-4dde-8499-955d2da08937). 


The dataset contains wind tunnel test data acquired for the validation of a new flutter test version of the Parametric Flutter Margin (PFM) method, specifically applied to wings undergoing large deflections. The PFM method adds a stabilising parameter, such as a stabilising mass, to the model such that the flutter velocity is increased. To demonstrate the method a wind tunnel test campaign was performed at TU Delft using the Delft Pazy Wing which can exhibit large nonlinear deflection. The wing was equipped with a flutter pod consisting of a shaker and stabilising mass that was placed at the mid-span position at the leading edge of the wing. During the test campaign, three test series were performed. The first identified the flutter boundary through direct flutter tests, with the flutter onset and offset velocities being determined by actually hitting flutter that turned into a Limit Cycle Oscillation (LCO). The second and third test series were the PFM measurements, where both Single Input Single Output (SISO) and Multiple Input Multiple Output (MIMO) PFM tests were applied to obtain the nominal flutter boundaries without actually hitting flutter.  


history
  • 2023-02-28 first online, published, posted
publisher
4TU.ResearchData
format
Code: .m, Dataset: .mat, Licenses: .txt
organizations
TU Delft, Faculty of Aerospace Engineering, Department of Aerospace Structures & Materials;
Technion—Israel Institute of Technology

DATA

files (2)