Summary
The present study concerns an experimental investigation of a passive shock/boundary layer interaction control system used on an airfoil. The passive control system is installed in the shock region and consists of a local porous part of the airfoil surface covering a small internal cavity. So the pressure jump through the shock wave is weakened by a natural fluid circulation through the porous plate, reducing the wave drag. At the same time, the viscous drag is increased, and wake measurements show that the total drag increases overall.
The first part of the study concerns pressure measurements on the model and in the wake for a varying angle of incidence at M=0.77 with and without control. The main part consists of velocity laser measurements around the passive control system and up to the trailing edge, with and without control to obtain boundary layer profiles and a far field quantification. The data constitutes a data base available for code validation.
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References
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© 1997 Friedr. Vieweg & Sohn Verlagsgesellschaft mbH, Braunschweig/Wiesbaden
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Archambaud, J.P., Rodde, A.M. (1997). Qualification by Laser Measurements of the Passive Control on the LVA-1A Airfoil in the T2 Wind Tunnel. In: Stanewsky, E., Délery, J., Fulker, J., Geißler, W. (eds) EUROSHOCK - Drag Reduction by Passive Shock Control. Notes on Numerical Fluid Mechanics (NNFM), vol 56. Vieweg+Teubner Verlag. https://doi.org/10.1007/978-3-322-90711-0_20
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DOI: https://doi.org/10.1007/978-3-322-90711-0_20
Publisher Name: Vieweg+Teubner Verlag
Print ISBN: 978-3-322-90713-4
Online ISBN: 978-3-322-90711-0
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