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Measurement of flow around a flap side with porous edge treatment

Measurement of flow around a flap side with porous edge treatment
Measurement of flow around a flap side with porous edge treatment
Wind tunnel experiments were performed to investigate a flap side-edge flowfield. A porous side-edge treatment was applied to a half span flap in an attempt to reduce the flap side-edge noise. Measurements taken were forces, on-surface pressures, particle image velocimetry, hotwire anemometry and on-surface microphones. Oil flow was performed to visualise the on-surface flow. Three potential acoustic sources were identified. The first two sources were the turbulent shear layer reattaching on the side-edge and on the upper surface. A mid-frequency broadband hump was measured by an on-surface microphone at the point of reattachment of the turbulent shear layer on the flap side edge. The third source was a low frequency instability in the vortex due to non-linear vortical interactions upstream of the flap. This instability was measured by a hotwire in the downstream vortex and by an on-surface microphone in the main element flap cove. The effect of the porous side-edge was to reduce the magnitude of vorticity in the turbulent shear layer and the vortex. It was most noticeable in reducing the mid frequencbroadband hump. It also had the effect of displacing the vortex further away from the flap surface. This reduced the magnitude of the low frequency perturbations from the unstable vortex that interacted with the solid surface.
Angland, D.
b86880c6-31fa-452b-ada8-4bbd83cda47f
Zhang, X.
3056a795-80f7-4bbd-9c75-ecbc93085421
Chow, L.C.
d0f85930-0d96-4ed5-98f3-9a04182e4274
Molin, N.
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Angland, D.
b86880c6-31fa-452b-ada8-4bbd83cda47f
Zhang, X.
3056a795-80f7-4bbd-9c75-ecbc93085421
Chow, L.C.
d0f85930-0d96-4ed5-98f3-9a04182e4274
Molin, N.
0bed184f-f112-4182-b266-cd630c2ba109

Angland, D., Zhang, X., Chow, L.C. and Molin, N. (2006) Measurement of flow around a flap side with porous edge treatment. 43rd AIAA Aerospace Sciences Meeting and Exhibit, United States. 09 - 12 Jan 2006. 21 pp . (doi:10.2514/6.2006-213).

Record type: Conference or Workshop Item (Paper)

Abstract

Wind tunnel experiments were performed to investigate a flap side-edge flowfield. A porous side-edge treatment was applied to a half span flap in an attempt to reduce the flap side-edge noise. Measurements taken were forces, on-surface pressures, particle image velocimetry, hotwire anemometry and on-surface microphones. Oil flow was performed to visualise the on-surface flow. Three potential acoustic sources were identified. The first two sources were the turbulent shear layer reattaching on the side-edge and on the upper surface. A mid-frequency broadband hump was measured by an on-surface microphone at the point of reattachment of the turbulent shear layer on the flap side edge. The third source was a low frequency instability in the vortex due to non-linear vortical interactions upstream of the flap. This instability was measured by a hotwire in the downstream vortex and by an on-surface microphone in the main element flap cove. The effect of the porous side-edge was to reduce the magnitude of vorticity in the turbulent shear layer and the vortex. It was most noticeable in reducing the mid frequencbroadband hump. It also had the effect of displacing the vortex further away from the flap surface. This reduced the magnitude of the low frequency perturbations from the unstable vortex that interacted with the solid surface.

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01 - AIAA 2006-0213_authors
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Published date: January 2006
Venue - Dates: 43rd AIAA Aerospace Sciences Meeting and Exhibit, United States, 2006-01-09 - 2006-01-12
Organisations: Aerodynamics & Flight Mechanics

Identifiers

Local EPrints ID: 42976
URI: https://eprints.soton.ac.uk/id/eprint/42976
PURE UUID: 713d811e-8958-4cd4-821f-073b517363e6

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Date deposited: 10 Jan 2007
Last modified: 13 Mar 2019 21:10

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