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Research of Real-time Measurement System and Problems in Compressible Flow Measurement for Seven-Hole Probes

Author: DingTao
Tutor: MingXiao
School: Nanjing University of Aeronautics and Astronautics
Course: Fluid Mechanics
Keywords: Seven -hole probe Real-time measurement Helicopter flow Computational Fluid Dynamics Flow field characteristics Compressible flow measurement Numerical calibration
CLC: V211.4
Type: Master's thesis
Year: 2008
Downloads: 174
Quote: 3
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Abstract


Current research aerodynamic performance measurements are an important way to measure the flow field seven-hole probe has its unique advantages. At present, research on the seven -hole probe also limited to low speed incompressible flow, and no corresponding ancillary test systems , making use of more cumbersome and time-consuming calibration . Based on Labview software and computational fluid dynamics method, the seven -hole probe real-time measurement systems and compressible flow measurements were studied. Labview software combines high precision pressure sensors and data acquisition card built seven -hole probe test system has a good user interface , simplifying the measurement process. In the belly of a helicopter models for real-time flow measurement results show that the system even when flying in harsh environment , good stability, high precision , to better reflect the real-time measuring the flow characteristics , to meet the measurement requirements. Articles using numerical methods for flow around a seven -hole probe were studied, analyzed the different angles of attack seven -hole probe head pressure distribution, flow lines, velocity vectors and other features, compared to 0.6 and 1.0 Mach leeward probe flow separation . The results showed that more than 30 degrees when the angle of attack , the probe head began to separate , as the angle of attack increases , to further expand the separation zone , the separation performance of open -type separator ; seven-hole probe in the case of a large angle of attack , axial separation zone along the probe is gradually increasing ; different Mach numbers , leeward zone separation zone is different. Using the numerical results of the seven -hole probe subsonic compressible flow calibration and measurement methods were studied , the results showed that the calibration flow angle fitting accuracy of 2% , the total static pressure inside and outside the region are not relative standard deviation more than 3 % higher than the same state of the experimental calibration accuracy. Finally, we discuss the seven -hole probe isentropic unknown supersonic flow measurement research direction, another draw , using the seven -hole pressure probe cone and cylinder Combining cross- surface temperature monitoring is to determine whether the flow supersonic key .

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CLC: > Aviation, aerospace > Aviation > Basic theory and experiments > Aerodynamics > Aircraft aerodynamics
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