TY - GEN
T1 - Stereo PIV measurements in a multi-stream, rectangular, supersonic jet
AU - Magstadt, Andrew S.
AU - Glauser, Mark N.
N1 - Publisher Copyright:
© 2018, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2018
Y1 - 2018
N2 - A test campaign has been carried out in which a complex jet field was experimentally investigated in an anechoic chamber. Stereo PIV measurements were acquired over a series of planar locations in this supersonic flow-field, simultaneously sampled with pressure transducers embedded in the jet and far-field microphones in the anechoic chamber. Due to the high mass flow rates (∼ 2.0 kg/s), nozzle pressure ratios (NPR = 4.25), and Reynolds number (Re = 2.74 ×106), various calibration challenges in the PIV instrumentation were encountered. The solutions employed to overcome these difficulties are first presented. After establishing confidence in the measurements, the full dataset is presented through planar and volumetric views. Statistical moments and Reynold stresses reveal a complex evolution of the turbulence and shock structures, which dominate this flow. By establishing the validity of the simultaneously acquired pressure and acoustic data, future studies will use this dataset in aeroacoustic analyses of the jet.
AB - A test campaign has been carried out in which a complex jet field was experimentally investigated in an anechoic chamber. Stereo PIV measurements were acquired over a series of planar locations in this supersonic flow-field, simultaneously sampled with pressure transducers embedded in the jet and far-field microphones in the anechoic chamber. Due to the high mass flow rates (∼ 2.0 kg/s), nozzle pressure ratios (NPR = 4.25), and Reynolds number (Re = 2.74 ×106), various calibration challenges in the PIV instrumentation were encountered. The solutions employed to overcome these difficulties are first presented. After establishing confidence in the measurements, the full dataset is presented through planar and volumetric views. Statistical moments and Reynold stresses reveal a complex evolution of the turbulence and shock structures, which dominate this flow. By establishing the validity of the simultaneously acquired pressure and acoustic data, future studies will use this dataset in aeroacoustic analyses of the jet.
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U2 - 10.2514/6.2018-0054
DO - 10.2514/6.2018-0054
M3 - Conference contribution
AN - SCOPUS:85141584567
SN - 9781624105241
T3 - AIAA Aerospace Sciences Meeting, 2018
BT - AIAA Aerospace Sciences Meeting
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA Aerospace Sciences Meeting, 2018
Y2 - 8 January 2018 through 12 January 2018
ER -