| 超声速大迎角条件下小展弦比弹翼压力分布计算研究 |
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| 引用本文： | 周岭,赵协和.超声速大迎角条件下小展弦比弹翼压力分布计算研究[J].实验流体力学,2002,16(1):104-107. |
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| 作者姓名： | 周岭 赵协和 |
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| 作者单位： | 中国空气动力研究与发展中心,四川,绵阳,621000 |
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| 摘 要： | 为计算超声速高M数及大迎角条件下小展弦比弹翼背风侧脱体涡消失后的压力分布 ,采用面元法及非线性压缩性修正方法 ,获得了与实验数据吻合较好的计算结果
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| 关 键 词： | 超声速 大迎角 展弦比 压缩性 压力分布 面元法 |
| 文章编号： | 1007-3124(2002)01-0104-04 |
| 修稿时间： | 2000年9月26日 |
Calculation of pressure distributions of low aspect ratio missile wings at supersonic speeds and high angles of attack |
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| ZHOU Ling,ZHAO Xie he.Calculation of pressure distributions of low aspect ratio missile wings at supersonic speeds and high angles of attack[J].Experiments and Measur in Fluid Mechanics,2002,16(1):104-107. |
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| Authors: | ZHOU Ling ZHAO Xie he |
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| Abstract: | A panel method with nonlinear compressibility correction is developed to calculate pressure distributions of low aspect ratio missile wings at high supersonic Mach numbers and high angles of attack. Good agreement between the calculated results and experimental data is obtained. |
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| Keywords: | supersonic flow high angles of attack aspect ratio nonlinear compressibility pressure distribution panel method |
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