広がりノズルから噴出される超音速噴流の境界層制御に関する研究(第2報)制御流のよどみ圧力の影響

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[synopsis] In this paper, it aimed to clarify the behavior and the flow field of a supersonic jet flow issuing from a divergent nozzle widely used in industry. Especially, the separation point of the flow was controlled by vertical control jets to the separated supersonic jet flow at the divergent part of the nozzle. By such a method, the boundary layer control of the supersonic jet flow issuing from the divergent nozzle was clarified. In this time, the flow field of the main jet flow has been clarified when the control jets were issued with various stagnation pressures. The control jets were vertically issued from eight small holes or four small holes for the main jet flow. Experiments and numerical analyses were completed when the stagnation pressure ratios of the main jet flow were given as Po/Pa ＝ 6.0 and the stagnation pressure ratio of the control jets were given as Pc/Pa ＝ 3.0, 6.0(eight holes) and Pc/Pa ＝ 3.0(four holes). Moreover, numerical analyses were also made when the stagnation pressure ratios of the control jets were given as Pc/Pa ＝ 10.0(eight holes) and Pc/Pa ＝ 6.0, 10.0(four holes). In the experiment, the total pressures were measured around the exit of the divergent nozzle and the equi-total pressure distributions were examined. In the numerical analysis, the velocity contours of the flow were examined for the inside of the divergent nozzle and the downstream region of the flow. As a result, the main jet flow issuing from the divergent nozzle becomes different patterns as the stagnation pressure ratios of the control jets are different when the amount of the control jets is eight. But the pattern of the main jet flow is the same one as the stagnation pressure ratios of the control jets are different when the amount of the control jets is four.
近畿大学工学部の論文

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児島忠倫
近畿大

広がりノズルから噴出される超音速噴流の境界層制御に関する研究(第2報)制御流のよどみ圧力の影響

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