Blockage effect on the flow around a cylinder probe in calibration |
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Authors: | WANG Hong-wei and WEI Jun |
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Institution: | National Key Laboratory on Aero-Engines, School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100083;National Key Laboratory on Aero-Engines, School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100083 |
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Abstract: | Flow around a 2-D cylinder pressure probe placed in uniform flow, free jet flow, and wind tunnel flow was analyzed with potential flow theory and simulated with numerical method. Blockage effect was investigated under several typical flow Mach numbers. The result from numerical simulation shows a similar trend to the one from potential flow method while varies in quantity. Wind tunnel walls accelerate the flow near the probe and thus produce a blockage effect;Boundary of free jet flow, however, decelerates the flow and thus produces a "negative" blockage effect. A maximum incoming Mach number exists when the probe is calibrated in wind tunnel in high subsonic condition due to choking caused by shocks and shock induced separation. The critical Mach number varies with blockage ratio, which makes high Mach number impossible to achieve in large blockage ratio condition. The blockage effect itself is unavoidable for calibration or measurement although a sufficiently small blockage ratio brings minor effect. Correction can be implemented based on the numerical simulation result presented in this paper and further works. |
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Keywords: | pressure probe blockage measurement error numerical simulation calibration probe flow around a cylinder effect Correction based paper works measurement small minor large critical maximum Mach number calibrated high condition choking shock |
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