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

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

Research output: Contribution to conferencePaperpeer-review

5 Citations (Scopus)


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 ef- fects. 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 tail- board, 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
Original languageEnglish
Number of pages11
Publication statusPublished - 08 Jan 2004
EventAIAA 42nd Aerospace Sciences Meeting & Exhibit - Reno, United States
Duration: 01 Jan 200401 Jan 2004


ConferenceAIAA 42nd Aerospace Sciences Meeting & Exhibit
Country/TerritoryUnited States


  • CFD
  • Transonic wind tunnel
  • Turbine cascade


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