| 导弹大攻角气动特性计算 |
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| 引用本文： | 董月娟. 导弹大攻角气动特性计算[J]. 战术导弹技术, 1995, 0(4): 10-17 |
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| 作者姓名： | 董月娟 |
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| 作者单位： | 中国航天工业总公司第三研究院 |
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| 摘 要： | 提出了一种适于在初步设计中使用、具有良好精度的亚、超音速导弹大攻角气动特性的工程计算方法。重点介绍翼－身，尾－身干扰对非线性法向力的贡献，并用抽样作算例，通过翼－身，尾－身干扰因子进行具体计算。结果表明这种方法具有简便，计算快和符合设计精度要求的优点。
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| 关 键 词： | 导弹 气动性能 大攻角 计算 |
COMPUTATION OF LARGE ATTACK ANGLE AERODYNMICS FOR MISSILE |
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| Dong YuejuanThe Third Rearch Academy of CASC. COMPUTATION OF LARGE ATTACK ANGLE AERODYNMICS FOR MISSILE[J]. Tactical Missile Technology, 1995, 0(4): 10-17 |
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| Authors: | Dong YuejuanThe Third Rearch Academy of CASC |
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| Affiliation: | Dong YuejuanThe Third Rearch Academy of CASC |
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| Abstract: | An engineering method of aerodynamical computation which apply to preliminary design of sub- sonic and supersonic missiles in large attack angle and have a good precision is presented.the contributions of wing-body and tail-body interference to the nonlinear normal force being stressecl.AS an example,wing-body and tail body interference factor are computed,the result indicate that the method is simple and meets the needs of precision. |
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| Keywords: | Missile Aerodynamic performance Attack angle |
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