| Citation: | LI Jiwei, LU Pan, WANG Qiu, et al. Experimental study of boundary-layer transition on a 7° sharp cone in shock tunnel[J]. Journal of Beijing University of Aeronautics and Astronautics, 2020, 46(11): 2087-2093. doi: 10.13700/j.bh.1001-5965.2019.0577(in Chinese)
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Hypersonic boundary layer transition has an important influence on friction drag and heat transfer, and thus accurate prediction and control of boundary layer transition are critical to the development of hypersonic vehicles. In this paper, experimental study on a 7° half-angle sharp cone was conducted in the JF8A shock tunnel to investigate the hypersonic boundary layer transition. The wall fluctuation pressure was measured by the pressure transducer with the response frequency as high as 1 MHz, and the development process of the disturbance wave in hypersonic sharp cone boundary layer was also investigated together with the results of heat flux measurement. The experimental results show that the pressure fluctuation in the free flow is 2.8% under the test condition of Reynolds number equals to 6.4×106/m. Structures and development of the second mode waves in the process of transition can be obtained by the high-frequency fluctuation pressure measurement technique. The characteristic frequency of the second mode wave changes from 165 kHz to 206 kHz under the present test condition. The current research results can provide data support for hypersonic numerical method validation.
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