Vortex investigation over a rolling delta wing model in transonic flow by stereo PIV measurements

Sammler, B.; Schröder, Andreas; Arnott, A.; Otter, Dirk; Agocs, Janos; Kompenhans, Jürgen

doi:10.1109/iciasf.2003.1274877

Cited by 7 publications

(1 citation statement)

References 3 publications

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“…Therefore, the particular considerations about remote control operation, equipment cooling, and so on are needed for the equipments in the chamber. Due to these difficulties, practical experiments of PIV measurements in transonic wind tunnels are limited [1], [2]. In the present study, a fully remote-controlled stereoscopic PIV system is developed for velocity measurement of transonic complex flows, and preliminary results using the system are reported to evaluate the system capabilities.…”

Section: Introductionmentioning

confidence: 99%

Stereoscopic PIV System Development for the JAXA 2m × 2m Transonic Wind Tunnel

Kato

Watanabe²,

Hashimoto³

et al.

ICIASF 2005 RecordInternational Congress onInstrumentation in AerospaceSimulation Facilities

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Stereoscopic PIV technique was applied to the JAXA next-generation supersonic transport (SST) jet experimental airplane model. The measurements have been performed in the JAXA 2m x 2m Transonic Wind tunnel. Application of PIV measurement techniques to transonic wind tunnels has particular difficulties associated with complex flows with shock waves. Due to these difficulties, practical experiments of PIV measurements in transonic wind tunnels are limited. In the present study, a fully remote-controlled stereoscopic PIV system is developed for velocity measurement of transonic complex flows, and preliminary results using the system are reported to evaluate the system capabilities. The tests were conducted at a freestream Mach number from 0.4 to 1.4 . An example of raw PIV images captured by the camera around the flow-through nacelle intake. Location and shape of shock waves observed in the PIV results are in good agreement with schlieren results for identical test condition. The velocity field information of the PIV results is valuable in a precise validation of CFD.

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Section: Introductionmentioning

confidence: 99%

Stereoscopic PIV System Development for the JAXA 2m × 2m Transonic Wind Tunnel

Kato

Watanabe²,

Hashimoto³

et al.

ICIASF 2005 RecordInternational Congress onInstrumentation in AerospaceSimulation Facilities

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show abstract

Combined application of pressure sensitive paint and particle image velocimetry to the flow above a delta wing

et al. 2007

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Recent Developments of Image Based Measurement Methods for Application to Transonic Flows in Industrial Wind Tunnels

Kompenhans

Agocs

Egami

et al. 2006

Chinese Journal of Aeronautics

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Vortex investigation over a rolling delta wing model in transonic flow by stereo PIV measurements

Cited by 7 publications

References 3 publications

Stereoscopic PIV System Development for the JAXA 2m × 2m Transonic Wind Tunnel

Stereoscopic PIV System Development for the JAXA 2m × 2m Transonic Wind Tunnel

Combined application of pressure sensitive paint and particle image velocimetry to the flow above a delta wing

Recent Developments of Image Based Measurement Methods for Application to Transonic Flows in Industrial Wind Tunnels

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Vortex investigation over a rolling delta wing model in transonic flow by stereo PIV measurements

Cited by 7 publications

References 3 publications

Stereoscopic PIV System Development for the JAXA 2m &#215; 2m Transonic Wind Tunnel

Stereoscopic PIV System Development for the JAXA 2m &#215; 2m Transonic Wind Tunnel

Combined application of pressure sensitive paint and particle image velocimetry to the flow above a delta wing

Recent Developments of Image Based Measurement Methods for Application to Transonic Flows in Industrial Wind Tunnels

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Product

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Stereoscopic PIV System Development for the JAXA 2m × 2m Transonic Wind Tunnel

Stereoscopic PIV System Development for the JAXA 2m × 2m Transonic Wind Tunnel