| 火箭及导弹的底阻计算方法及其CRMBP程序 |
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| 引用本文： | 赵鹤书,王强.火箭及导弹的底阻计算方法及其CRMBP程序[J].北京航空航天大学学报,1993(1):27-33. |
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| 作者姓名： | 赵鹤书 王强 |
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| 作者单位： | 北京航空航天大学流体力学研究所
(赵鹤书)，北京航空航天大学流体力学研究所(王强) |
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| 摘 要： | 本文叙述了作者开发的基于Chapman-Korst理论的超音速底部压强计算方法及其计算程序CRMBP。该方法及程序计及了喷流、喷管和火箭后体多种参数的影响,以及羽流诱导分离情况。计算结果与实验结果符合得较好,特别是冷喷流情况。本文的方法及其程序可供设计部门作设计计算及参数分析使用。
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| 关 键 词： | 底部压强 超音速 阻力 喷管流动 |
COMPUTATIONAL METHOD FOR BASE PRESSURE OF MISSILES AND THE BRIEF OF ITS CRMBP CODE |
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| Zhao Heshu Wang Qiang.COMPUTATIONAL METHOD FOR BASE PRESSURE OF MISSILES AND THE BRIEF OF ITS CRMBP CODE[J].Journal of Beijing University of Aeronautics and Astronautics,1993(1):27-33. |
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| Authors: | Zhao Heshu Wang Qiang |
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| Institution: | Research Inst. of Fluid Mechanics |
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| Abstract: | Computational method,based on chapman-Korst theory,of supersonic base pressure with an exhaust jet and the function of its code are described. The method takes into account the effects of a variety of parameters concerning jet, nozzle and afterbody of a missile. The comprison between computations and experiments is coincident,expecially for cold jet. The method can be used as a predictive tool. |
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| Keywords: | base pressure supersonic drag jet |
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