| 火箭级间分离喷流干扰数值模拟与风洞试验研究 |
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| 引用本文： | 王志坚,伍贻兆,林敬周.火箭级间分离喷流干扰数值模拟与风洞试验研究[J].空气动力学学报,2010,28(2). |
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| 作者姓名： | 王志坚 伍贻兆 林敬周 |
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| 作者单位： | 1. 南京航空航天大学航空宇航学院,江苏,南京,210016
2. 中国空气动力研究与发展中心,四川,绵阳,621000 |
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| 摘 要： | 针对典型风洞试验状态,采用有限体积法求解三维雷诺平均Navier-Stokes(RANS)方程,数值模拟了给定级间距下火箭级间分离喷流干扰流动情况,获得了清晰的流场结构和有/无喷流干扰时两级气动特性变化规律,并对仅主机喷流和主机与四游机同时喷流的情况进行了计算,数值模拟研究结果为风洞试验方案的设计提供了参考依据。在典型状态数值模拟研究的基础上采用了冷喷流模拟技术对多个状态下火箭级间分离喷流干扰特性进行了风洞试验研究,获得了两级在有/无喷流、同轴变攻角情况下的气动力系数,研究结果表明,级间喷流干扰会对两级气动特性带来较大影响。相同状态下计算得到的两级气动特性变化与试验符合较好,表明了针对风洞试验状态的预先数值模拟对试验方案的设计验证可提供有益的参考。
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| 关 键 词： | 高超声速 数值模拟 风洞试验 级间分离 喷流干扰 |
Numerical simulation and wind tunnel test research on rocket stage-separation jet flow interaction |
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| WANG Zhi-jia,WU Yi-zhao,LIN Jing-zhou.Numerical simulation and wind tunnel test research on rocket stage-separation jet flow interaction[J].Acta Aerodynamica Sinica,2010,28(2). |
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| Authors: | WANG Zhi-jia WU Yi-zhao LIN Jing-zhou |
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| Institution: | 1.College of Aerospace Engineering/a>;Nanjing University of Aeronautics and Astronautics/a>;Nanjing 210016/a>;China/a>;2.China Aerodynamics Research & Development Center/a>;Mianyang 621000/a>;China |
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| Abstract: | The paper presents wind tunnel test and numerical simulation research on aerodynamics of rocket during stage separation.Finite volume method is used to calculate the three-dimensional Reynolds-averaged Navier-Stokes equations in this paper.The typical stage-separation flow field of rocket is simulated,and reasonable flow structure is obtained.The numerical results show the aerodynamic characteristics variations of first and second stages and they conformed well to the experimental data.That the results with... |
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| Keywords: | hypersonic flow numerical simulation wind tunnel test stage separation jet flow interaction aerodynamic characteristics |
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