Summary
For an experimental study of the flow on a rectangular wing with rear separation the half-model technique was applied. Below stall unsymmetrical flow conditions due to the displacement effect of the interferent boundary layers on the wing-reflection wall intersection can be minimized by boundary layer suction. Beyond stall the interacting vortex sheets, caused by separation of the three-dimensional boundary layers on the wing and the reflection wall, form a vortex system which is different from that develo** on the corresponding full model. The topological structure of this vortex system and its effect on the flow symmetry are discussed.
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References
Bippes, H.; Jacob, K.; Turk, M.: Experimentelle Untersuchung’ zur abgelösten Strömung an einem Rechteckflügel. DFVLR-FB 81–12 (1981).
Hornung, H.; Perry, A.E.: Streamsurface Bifurcation, Vortex Skeletons and Separations. DFVLR-IB 222–82 A 25 (1982).
Winkelmann, A.; Barlow, B.: Flowfield Model for a Rectangular Planform Wing beyond Stall, AIAA-Journal, Vol. 18, No. 8, August 1980, pp. 1006–1008.
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© 1982 Springer-Verlag Berlin Heidelberg
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Bippes, H., Turk, M. (1982). Half Model Testing Applied to Wings above and below Stall. In: Haase, W. (eds) Recent Contributions to Fluid Mechanics. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-642-81932-2_3
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DOI: https://doi.org/10.1007/978-3-642-81932-2_3
Publisher Name: Springer, Berlin, Heidelberg
Print ISBN: 978-3-642-81934-6
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