| Citation: | JIANG Lusheng, CAO Yaxiong, LIU Ting, et al. Experimental and computational study on blade surface pressure measurement of coaxial rigid rotor in hovering state[J]. Journal of Beijing University of Aeronautics and Astronautics, 2021, 47(12): 2484-2493. doi: 10.13700/j.bh.1001-5965.2020.0669(in Chinese)
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For the coaxial rigid model rotor in hovering state, the experimental and numerical simulation research on blade surface pressure measurement were carried out. The micro pressure sensor was used to measure the blade surface pressure, which not only obtains the experimental data of blade surface pressure, but also provides verification data for CFD method to calculate the blade surface pressure. The calculation results are in good agreement with the experimental results, which verifies the effectiveness of CFD method. The flow and pressure characteristics of the upper and lower rotor blade surface of the coaxial rigid rotor were obtained. The results show that, for coaxial rigid rotor with 4 upper blades and 4 lower blades, the blade surface pressure changes periodically with the rotation of the blade, and there are eight small cycles in one rotation cycle. In the hovering state of the upper and lower torque balancing, most of the area of the lower rotor blade is affected by the downwash flow, and the profile pull of the lower rotor is lower than that of the upper rotor; total pitch angle of the lower rotor in the tip region is larger than that of the upper rotor, and affected by respective upwash flow, the profile pull of the lower rotor is higher than that of the upper rotor.
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