An investigation of vortex breakdown at Mach 2

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dc.creator Craven, A. H.
dc.creator Alexander, A. J.
dc.date 2017-07-13T15:09:39Z
dc.date 2017-07-13T15:09:39Z
dc.date 1963-11
dc.date.accessioned 2020-11-30T18:29:56Z
dc.date.available 2020-11-30T18:29:56Z
dc.identifier.uri https://reports.aerade.cranfield.ac.uk/handle/1826.2/4139
dc.identifier.uri http://dspace.lib.cranfield.ac.uk/handle/1826/12187
dc.identifier.uri https://reports.aerade.cranfield.ac.uk/handle/1826.2/4139
dc.identifier.uri http://dspace.lib.cranfield.ac.uk/handle/1826/12187
dc.description Wind tunnel tests have been made at M = 2 on a 75° swept delta wing in order to study the progressive breakdown of the leading edge vortices, which occurs at high incidence. The incidence at which vortex breakdown occurred at supersonic speeds was somewhat less than at low speeds, but the pattern of breakdown appeared to be similar, although the spiralling region of flow is much larger at supersonic speeds. Quite slender objects placed downstream of the wing had appreciable upstream effects, causing vortex breakdown to move upstream by as much as 20% of the root chord for the same incidence.
dc.description.abstract Wind tunnel tests have been made at M = 2 on a 75° swept delta wing in order to study the progressive breakdown of the leading edge vortices, which occurs at high incidence. The incidence at which vortex breakdown occurred at supersonic speeds was somewhat less than at low speeds, but the pattern of breakdown appeared to be similar, although the spiralling region of flow is much larger at supersonic speeds. Quite slender objects placed downstream of the wing had appreciable upstream effects, causing vortex breakdown to move upstream by as much as 20% of the root chord for the same incidence.
dc.language en
dc.publisher College of Aeronautics
dc.relation CoA/N/AERO-158
dc.relation 158
dc.title An investigation of vortex breakdown at Mach 2
dc.type Report
dc.type Report


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