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
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