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Configuration of Shock Waves in Two-Dimensional Overexpanded Jets

Journal of Thermal Science 2003年第4期12卷 294-298页

作者： Masashi Kashitani Yutaka Yamaguchi Yoshiaki Miyazato Mitsuharu Masuda Kazuyasu Matsuo Department of Aerospace Engineering National Defense Academy 1-10-20 Hashirimizu Yokosuka Kanagawa 239-8686 JapanDepartment of Aerospace Engineering National Defense Academy 1-10-20 Hashirimizu Yokosuka Kanagawa 239-8686 JapanDepartment of Energy and Environmental Engineering Kyushu University 6-1 Kasuga-Kouen Kasuga Fukuoka 816-8580 JapanDepartment of Energy and Environmental Engineering Kyushu University 6-1 Kasuga-Kouen Kasuga Fukuoka 816-8580 JapanDepartment of Mechanical Systems and Environmental Engineering The University of Kitakyushu 1-1 Hibikino Wakamatsu-ku Kitakyushu Fukuoka 808-0315 Japan

An experimental and analytical study has been carried out to obtain the clear understanding of a shock wave transition associated with a steady two-dimensional overexpanded flow. Two-dimensional inviscid theory with respect to a shock wave reflection is used in the present study on the characteristic of shock waves. The results obtained from the flow analysis are compared with those obtained from flow visualizations. It is shown that in the region of regular reflection, the angle of an incident shock wave becomes lower than that calculated by two shock theory with an increment in the ratio PJPb of the nozzle exit pressure Pc to the back pressure Pb. It is indicated that the configuration of shock waves in overexpanded jets is influenced by the divergent angle at the nozzle exit. Also it is shown from the flow visualization that a series of shock waves move into the nozzle inside with a decrease in pressure ratio Pc/Pb, even if the Pc/Pb is under overexpanded conditions.

关键词：振动波超声喷管可压缩流体膨胀喷射空气动力学

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