Experimental characterisation of flutter and divergence of 2D wing section with stabilised response

J. Sodja*, F. Roizner, R. De Breuker, M. Karpel

*Corresponding author for this work

Research output: Contribution to journalArticleScientificpeer-review

17 Citations (Scopus)


The first experimental application of the Parametric Flutter Margin method for identification of aeroelastic instabilities is presented. The experiment was performed in two steps using a two degree-of-freedom wing segment mounted in the wind tunnel. First, the reference flutter and divergence conditions were found by increasing the free-stream velocity until the observed response diverged. Then, the system was stabilised according to the Parametric Flutter Margin methodology, and the flutter and divergence conditions of the original test model were identified positively while being in a stable regime demonstrating excellent agreement with the reference instability conditions. Although the new experimental methodology is not model based, the results were compared with a theoretical model showing good agreement as well. The acquired data demonstrates both the accuracy of the Parametric Flutter Margin method as well as its capability to test for aeroelastic instabilities, both flutter and divergence, in stable and predictable testing conditions.

Original languageEnglish
Pages (from-to)542-552
Number of pages11
JournalAerospace Science and Technology
Publication statusPublished - 1 Jul 2018


  • Aeroelasticity
  • Characterisation
  • Divergence
  • Flutter
  • Parametric flutter margin
  • Wind tunnel experiment


Dive into the research topics of 'Experimental characterisation of flutter and divergence of 2D wing section with stabilised response'. Together they form a unique fingerprint.

Cite this