The in uence of a cavity on the steady and unsteady local pressure di??erence over a NACA0018 airfoil is investigated experimentally and compared to numerical calculations. In the experiments a new experimental method is used, which allows Strouhal numbers at which self-sustained oscillation of cavity ows is expected. The airfoil is ??xed to the wind tunnel and the ow is modulated transversally to the main ow by an acoustic standing wave generated by loudspeakers. The objective is obtain insight into the dynamical behavior of an airfoil with a cavity by comparison of experimental data to the results of a two- dimensional numerical Euler code. In the Strouhal range from 2.5 up to 10, based on the semi-chord, both experiment and numerical simulation do not show a strong e??ect of the cavity on the dynamical response of the wing. This response is dominated by the added mass of the wing.
|Title of host publication||Proceedings of the 47th AIAA Aerospace Sciences Meeting, 5-8 January, 2009, Orlando, Florida, USA|
|Place of Publication||Orlando, USA|
|Publisher||American Institute of Aeronautics and Astronautics Inc. (AIAA)|
|Publication status||Published - 2009|
|Event||47th AIAA Aerospace Sciences Meeting, January 5-8, 2009, Orlando, FL, USA - Orlando, FL, United States|
Duration: 5 Jan 2009 → 8 Jan 2009
|Conference||47th AIAA Aerospace Sciences Meeting, January 5-8, 2009, Orlando, FL, USA|
|Period||5/01/09 → 8/01/09|
Olsman, W. F. J., Osch, van, M. M. E., Hirschberg, A., Trieling, R. R., & Willems, J. F. H. (2009). Local pressure difference over a NACA0018 Airfoil with cavity using acoustic forcing. In Proceedings of the 47th AIAA Aerospace Sciences Meeting, 5-8 January, 2009, Orlando, Florida, USA American Institute of Aeronautics and Astronautics Inc. (AIAA).