| 引用本文: | 王正华,陈兰,王承尧.底部带姿控发动机的飞行器气动力计算.[J].国防科技大学学报,1993,15(2):6-10.[点击复制] |
| Wang Zhenghua,Chen Lan,Wang Chengyao.The Pneumatic Computation of Aerobat with Steering Control Engines at the Base[J].Journal of National University of Defense Technology,1993,15(2):6-10[点击复制] |
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| 底部带姿控发动机的飞行器气动力计算 |
| 王正华, 陈兰, 王承尧 |
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(航天技术系)
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| 摘要: |
| 本文提出了一种新的底部带姿控发动机的飞行器气动力计算方法。该方法将 S. C. Ward 的工程方法与作者近年来发展起来的底部带横向喷流的超音速强干扰流场的轴对称数值模拟方法有机地结合在一起，能给出喷流产生的包括直接、间接两部分在内的总推力和附加的俯仰力矩系数和偏航力矩系数。与无喷射的情形相比，底部阻力系数CD减小了。 |
| 关键词: 三维流动，底部流，强干扰，气动力汁算 |
| DOI： |
| 投稿日期：1992-02-20 |
| 基金项目: |
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| The Pneumatic Computation of Aerobat with Steering Control Engines at the Base |
| Wang Zhenghua, Chen Lan, Wang Chengyao |
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(Department of Aerospace Technology)
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| Abstract: |
| In this paper，a new method is presented for the pneumatic computation of aerobat with steering control engines at the base. The method is an organic combination of S. C. Ward's engineering method and the axisymmetric numerical simulation method developed by the authors earlier for the supersonic strong interaction flow field with transverse injection at the base. It can estimate the total propulsive forces and the additional pitching and yawing momentum coefficients，including both direct and indirect parts. The base drag coefficient CD decreases as compared with the case without injection. |
| Keywords: three dimensional flow,base flow,strong interaction,pneumatic computation |
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