This paper was published as Proceedings of the 43rd AIAA Aerospace Sciences Meeting and Exhibit, Reno, NV, USA, 10-13 January, 2005, pp. 1-12. It is also available from http://www.aiaa.org/.Linear cascade transonic wind tunnels with an open jet test section can suffer from\ud pitchwise end-wall interference. This causes a loss of pitchwise periodicity in the cascade,\ud increasing the uncertainty in the measurements and producing less accurate estimates of\ud turbine stage performance, flow exit angle and loss coefficient. To reduce the end-wall\ud interference, a slotted tailboard is tested in a transonic cascade run off-design, in a regime\ud at which the profile trailing edge shocks produce substantial reflections in the absence of\ud a suitable end-wall treatment. The tailboard is optimised by numerical modelling for an\ud isentropic discharge Mach number of 1.27. Tests over the wider isentropic Mach number\ud range 1:20 ≤ Mi ≤ 1:32 quantify the restored periodicity gained by the use of this tailboard.\ud When the tailboard is used away from its design point of Mi = 1:27, the discharge remains\ud more periodic than with an open jet test section. The tailboard performance varies nonmonotonically\ud away from its design point, driven by complex changes in the discharge wave\ud pattern. Some of these changes are identified by schlieren flow visualisation
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