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

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conference contribution
posted on 2008-02-04, 14:32 authored by Aldo Rona, Renato Paciorri, Marco Geron, N.Z. Ince
Transonic tests in linear cascade wind tunnels can suffer from significant test section boundary interference effects in pitch. A slotted tailboard has been designed and optimised with an in-house Euler numerical method to reduce such effects. Wind tunnel measurements on an overspeed Mach 1.27 discharge from a Rolls-Royce T2 cascade, featuring strong end-wall shock-induced interference, showed a 77% reduction in the flow pitchwise periodicity error with the optimised tailboard, with respect to the baseline open-jet cascade flow. Two-dimensional Euler predictions were also cross-validated against a three-dimensional Reynolds averaged computation, to explore the three-dimensionality of the discharge.

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Citation

Proceedings of the 42nd AIAA Aerospace Sciences Meeting and Exhibit, Reno, NV, USA, 5-8 January, 2004, pp. 1-11

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Proceedings of the 42nd AIAA Aerospace Sciences Meeting and Exhibit

Available date

2008-02-04

Notes

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=298

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en

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