| 反向喷流与主流干扰数值模拟 |
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| 引用本文： | 周伟江,马汉东.反向喷流与主流干扰数值模拟[J].空气动力学学报,1994,12(3):295-300. |
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| 作者姓名： | 周伟江 马汉东 |
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| 作者单位： | 北京空气动力研究所 |
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| 摘 要： | 反向喷流是改变钝体迎风面压力和温度分布的有效手段之一，所以了解反向喷流场对再入体防热及减阻设计具有重要意义，本文用有差分法求解轴称Ｎ－Ｓ方程模拟了球柱体部反向喷流与超声速自由来流的干扰流场。研究了喷流出口压力对流场的影响，物面压力分布及喷流Ｍａｃｈ盘、弓形激波的脱体距离与实验值进行了比较，取得了一致的结果，喷流附近分离区的再附位置及再附产生的激波位置也与实验相符，但高压比下再附激波略强于实验。
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| 关 键 词： | 反向喷流 分离流动 数值模拟 飞机 |
Numerical Simulation of the Interaction Between a Supersonsic stream and Countering Nosejet |
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| Zhou Weijiang, Ma Handong ,Li Feng, Deng Ningfeng.Numerical Simulation of the Interaction Between a Supersonsic stream and Countering Nosejet[J].Acta Aerodynamica Sinica,1994,12(3):295-300. |
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| Authors: | Zhou Weijiang Ma Handong Li Feng Deng Ningfeng |
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| Institution: | Beijing Institute of Aerodynamics |
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| Abstract: | The counterflow nosejet in supersonic flow is an importantmeans for modifying the pressure or temperature distributions on forward facing surfaces,and for protecting the nose from ablation.The flowfield resulting from a sonic nosejet with various jet pressure issuing into a supersonic stream are studied numerically. The nosejet has a nozzle diam-eter equal to 0.132 cylinder diameter, and main stream has a Mach num-ber of 2.5.The pressure distributions along nose surface and the loca-tions of Mach disk and bow shock are compared with experiment data, good agreement is presented.Various flowfield features are discussed. |
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| Keywords: | countering nosejet separated flow numerical simulation |
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