Summary
An experiment at high subsonic speeds on a two-dimensional aerofoil model is described, with a passive system for the control of shock waves via a porous skin and under-surface cavity. Passive control utilises the pressure gradient across the shock wave to induce a secondary flow through the surface and underlying cavity, causing injection into and suction from the boundary layer upstream and downstream of the shock wave, respectively. The displacement surface so formed induces compression waves which weaken the main shock wave, thereby reducing wave drag.
The measurements show that while passive control apparently reduces wave drag it also significantly increases viscous drag, consequently increasing drag overall.
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© 1997 Friedr. Vieweg & Sohn Verlagsgesellschaft mbH, Braunschweig/Wiesbaden
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Fulker, J.L., Simmons, M.J. (1997). An Experimental Investigation of Passive Shock/Boundary-Layer Control on an Aerofoil. 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_22
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DOI: https://doi.org/10.1007/978-3-322-90711-0_22
Publisher Name: Vieweg+Teubner Verlag
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Online ISBN: 978-3-322-90711-0
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