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Slot width augmentation in a slotted-wall transonic linear cascade wind tunnel

By Aldo Rona, Renato Paciorri, Marco Geron and N.Z. Ince

Abstract

This paper was published as Proceedings of the 42nd AIAA Aerospace Sciences Meeting and Exhibit, Reno, NV, USA, 5-8 January, 2004, pp. 1-11. It is also available from http://www.aiaa.org/content.cfm?pageid=298Transonic tests in linear cascade wind tunnels can suffer\ud from significant test section boundary interference effects in\ud pitch. A slotted tailboard has been designed and optimised\ud with an in-house Euler numerical method to reduce such effects.\ud Wind tunnel measurements on an overspeed Mach 1.27\ud discharge from a Rolls-Royce T2 cascade, featuring strong\ud end-wall shock-induced interference, showed a 77% reduction\ud in the flow pitchwise periodicity error with the optimised tailboard,\ud with respect to the baseline open-jet cascade flow.\ud Two-dimensional Euler predictions were also cross-validated\ud against a three-dimensional Reynolds averaged computation,\ud to explore the three-dimensionality of the discharge

Year: 2004
OAI identifier: oai:lra.le.ac.uk:2381/3473

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