| 跨音速喷管流动的数值模拟 |
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| 引用本文： | 唐安民,林同骥,浦群.跨音速喷管流动的数值模拟[J].航空学报,1993,14(8):344-349. |
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| 作者姓名： | 唐安民 林同骥 浦群 |
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| 作者单位： | 中国科学院力学研究所，中国科学院力学研究所，中国科学院力学研究所 北京 100080，北京 100080，北京 100080 |
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| 摘 要： | 数值方法采用的差分格式是具有高分辨率和快速稳定收敛性质的全变差衰减(TVD)格式。喷管壁面形状和反压可任意给定,对于典型轴对称与二维喷管(即壁面由收缩角为45°,扩张角为15°的两条直线用圆弧光滑连接而成。圆弧的无量纲半径等于0.625,其参考长度为喉道半宽),进行了有激波与无激波流动的数值模拟。计算结果与实验结果以及其他计算结果符合良好,此法可推广到非定常跨音速喷管流动的计算,并可用于工程中喷管设计。
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| 关 键 词： | 跨音速流功 喷管 差分法 激波 |
NUMERICAL SIMULATION OF TRANSONIC NOZZLE FLOW |
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| Tang An-min,Lin Tong-ji. Pu Qun.NUMERICAL SIMULATION OF TRANSONIC NOZZLE FLOW[J].Acta Aeronautica et Astronautica Sinica,1993,14(8):344-349. |
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| Authors: | Tang An-min Lin Tong-ji Pu Qun |
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| Institution: | Institute of Mechanies. Academia Sinica, Beijing, 100080 |
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| Abstract: | In this paper a method is given for calculating transonic nozzle flow with arbitrary nozzle wall shape and arbitrary back pressure by Total Variation Diminishing (TVD) scheme because oi its high accuracy and rapid convergence. The results of axisymmetrical and plane nozzle flow fields, shock and shock tree flow fields are obtained for a typical nozzle of two straight lines with convergent angle of 45° . divergent angle of 15° respectively connected smoothly with a circular arc whose non-dimensional radius of curvature is 0.625. The numerical results are in good agreement with experimental results and other numerical results. This method can be extended to unsteady transonic nozzle flow calculations and used for nozzle design of engineering application |
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| Keywords: | transonic Flow nozzle difference methods shock |
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