Wind tunnel wall interference effects on an oscillating aerofoil in the stall regime

Jie Cheng, M. H. Lowenberg, Xiao Ming Wangz, Ji Yan Yux

Research output: Chapter in Book/Report/Conference proceedingConference Contribution (Conference Proceeding)

1 Citation (Scopus)


In order to extract aerodynamic data from multi-degree-of-freedom wind tunnel tests, it is necessary to account for various interference effects, including those of the tunnel walls. As a precursor to developing a technique for estimating wall interference effects in 3 dimensions, a 2D aerofoil undergoing oscillations in the stall regime is investigated and a means of accounting for the wall interference proposed. Computational fluid dynamics is utilized to obtain the aerodynamic load and its accuracy is assessed by comparison with published experimental data. Besides comparing the pressure distribution and lift force loops, a five parameter Leishman-Beddoes model is identified to fit the computational results. For dynamic experiments, the pressure augmentation is accompanied by an increase in lift slope during the up stroke. When tunnel wall height increases, the capability of tracking static lift tends to be improved and the model overshoot reduces. The present methodology proves to be a reliable approach to evaluate the interference of tunnel walls for 2D wings, and could be used to extrapolate the wind tunnel data to generate a free flight aerodynamic model with a good degree of efficiency and accuracy.

Original languageEnglish
Title of host publication33rd AIAA Applied Aerodynamics Conference
PublisherAmerican Institute of Aeronautics and Astronautics Inc. (AIAA)
ISBN (Print)9781624103636
Publication statusPublished - 2015
Event33rd AIAA Applied Aerodynamics Conference, 2015 - Dallas, United States
Duration: 22 Jun 201526 Jun 2015


Conference33rd AIAA Applied Aerodynamics Conference, 2015
Country/TerritoryUnited States


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