航技研6.5m×5.5m低速風洞におけるステレオPIVシステム開発予備試験

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  • Preliminary test of stereo PIV system applied to the 6.5 m x 5.5 m low speed wind tunnel

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Preliminary tests of a stereo PIV system applied to a large-scale, low-speed wind tunnel are conducted. A tip vortex generated by a rectangular wing with an angle of attack and interfered flowfield between jet-engine exhaust and external flow are demonstratively measured by an off-the-shelf PIV system to examine the applicability of the stereo PIV technique to the large-scale wind tunnel and to acquire data required to determine the specifications of the system. The test results proved applicability of the stereo PIV to the large-scale, low-speed wind tunnel, while accuracy evaluation is to be done extensively in future. It was also found that the vibration of the wind tunnel has little effects on the velocity measurement accuracy while it does have effects on the location of the imaging area.

資料番号: AA0047429001

レポート番号: JAXA-SP-03-004

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