Quantitative study of unsteady compressible flow on an oscillating airfoil
- 1 July 1994
- journal article
- Published by American Institute of Aeronautics and Astronautics (AIAA) in Journal of Aircraft
- Vol. 31 (4) , 892-898
- https://doi.org/10.2514/3.46576
Abstract
The article of record as published may be found at http://dx.doi.org/10.2514/3.46576Real-time interferometric measurements of the flow near the leading edge of an oscillating airfoil offer detailed experimental quantification of the locally compressible flowfield that surrounds an oscillating airfoil at moderate subsonic Mach numbers. Interferograms obtained by a specially adapted real-time point-diffraction interferometry technique have revealed some important characteristics of this complex, and very rapidly varying, locally supersonic flow. Instantaneous pressure distributions determined from these interferograms document the effect of unsteadiness on the leading-edge flow environment.AFOSR-ISSA-89-0067AFOSR-MIPR-90-0012NAVAIRARO MIPR-ARO-132-9Keywords
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