| 引用本文: | 冯军红,鲁军勇,李开,等.电磁发射超高速弹丸气动特性数值分析.[J].国防科技大学学报,2022,44(1):92-98.[点击复制] |
| FENG Junhong,LU Junyong,LI Kai,et al.Numerical analysis for aerodynamic characteristics of electromagnetic launch hypervelocity projectile[J].Journal of National University of Defense Technology,2022,44(1):92-98[点击复制] |
|
| |
|
|
| 本文已被：浏览 5830次 下载 4756次 |
| 电磁发射超高速弹丸气动特性数值分析 |
| 冯军红,鲁军勇,李开,李湘平 |
|
(海军工程大学 舰船综合电力技术国防科技重点实验室, 湖北 武汉 430033)
|
| 摘要: |
| 采用数值计算方法研究了超高速弹丸的气动流场特性,重点分析了弹丸再入段的气动流场特性。利用风洞试验数据验证了S-A和k－ω SST湍流模型的预测精度,计算结果表明,在法向力预测上,两种湍流模型的预测精度较高,均在2%以内。在轴向力预测上,S-A湍流模型的预测精度较高,误差约为4.6%。当弹丸以大攻角再入时,弹丸横流效应较为明显,迎风面由于激波作用使得弹丸表面压力急剧增大,而背风面形成脱落的大尺度流向涡结构,导致压力减小,其中,迎风面的压力增大对弹丸气动系数影响更大。大攻角下的弹丸气动阻力和升力系数呈现明显的非线性,阻力系数明显增大,而且弹丸的静稳定裕度也急剧降低,使得弹丸的收敛特性变差,这是引起弹丸再入段速度衰减的主要原因。 |
| 关键词: 超高速弹丸 湍流模型 气动特性 大攻角 流向涡 |
| DOI：10.11887/j.cn.202201014 |
| 投稿日期：2020-07-01 |
| 基金项目:国家自然科学基金资助项目(51925704,51877214)；湖北省自然科学基金资助项目(2019CFB373) |
|
| Numerical analysis for aerodynamic characteristics of electromagnetic launch hypervelocity projectile |
| FENG Junhong, LU Junyong, LI Kai, LI Xiangping |
|
(National Key Laboratory of Science and Technology on Vessel Integrated Power System, Naval University of Engineering, Wuhan 430033, China)
|
| Abstract: |
| The numerical method was used to study the aerodynamic flow field characteristics of hypervelocity projectiles, especially in the reentry phase. The prediction accuracy of S-A and k－ω SST turbulence model was verified by wind tunnel test data. The calculation results show that the prediction accuracy of the two turbulence models is higher than 2% in normal force prediction. In axial force prediction, the S-A turbulence model has a high prediction accuracy of 4.6%. When the projectile reenters at a large angle of attack, the transverse flow effect of projectile is more obvious. The shock wave makes the surface pressure of the projectile increase sharply on the windward side, while the large-scale streamwise vortex structure formed on the leeward side reduces the pressure, and the increase of the pressure on the windward side has a greater impact on the aerodynamic coefficient of projectile. The aerodynamic drag and lift coefficient at high angle of attack are obviously nonlinear, the drag coefficient is obviously increased, and the static stability margin is also sharply reduced, which makes the convergence characteristics of projectile worse, and that is treated as the main reason for the velocity attenuation during the reentry process of projectile. |
| Keywords: hypervelocity projectile turbulence models aerodynamic characteristics large angle of attack streamwise vortices |
|
|
|
|
|
