飞机尾喷流诱导速度建模与仿真

杨立波; 丛岩

飞机尾喷流诱导速度建模与仿真

杨立波^1,,
丛岩²

1.
广东科技学院，广东东莞 523083
2.
空军航空大学，吉林长春 130000

基金项目:

东莞市社会科技发展（一般）项目 2019507154529

详细信息

作者简介:
杨立波（1981-），男，黑龙江木兰县人，汉族，硕士，副教授，研究方向为智能控制技术。E-mail：yanglibo_1981ylb@163.com

中图分类号: TJ7
计量
- 文章访问数: 152
- HTML全文浏览量: 80
- PDF下载量: 27
- 被引次数: 0
出版历程
- 收稿日期: 2020-03-19
- 修回日期: 2020-04-28
- 刊出日期: 2021-10-20

Modeling and Simulation of Jet-and Wake-Flow-Induced Velocity of Aircraft

YANG Libo^1
,,
CONG Yan²

1.
Guangdong University of Science and Technology, Dongguan 523083, China
2.
Air Force Aviation University, Changchun 130013, China

摘要

摘要: 本文对飞机尾喷流诱导速度进行了仿真研究。建立了飞机尾涡模型以及尾喷口喷流模型，并仿真了飞机流场中的诱导速度。然后应用CFD（computational fluid dynamics）对飞机的流场进行计算，并将CFD计算结果与尾喷流模型计算结果进行对比。仿真对比结果表明：飞机尾后100 m区域内，尾涡模型计算结果误差较大，此时应采用CFD对尾流场进行计算；而在尾后100 m区域外尾涡模型与CFD计算结果较为一致，尾涡模型的计算结果能够达到精度要求。
- 尾喷流 /
- 诱导速度 /
- 尾涡模型 /
- 喷流模型 /
- CFD
Abstract: The jet-and wake-flow-induced velocities of aircraft were analyzed in this study. Wake vortex and jet flow models were established, and the induced velocity of the aircraft was simultaneously simulated in the wake flow field. Then, the flow field of the aircraft was computed via computational fluid dynamics(CFD), the results of which were compared with those of the wake vortex models. The comparison showed that the errors computed using the wake vortex models were large, which suggests that the wake flow field should be computed via CFD within 100 m of the aircraft tail; these results are consistent with the CFD results beyond 100 m from the aircraft tail, and the wake vortex models meet the accuracy requirements.
- jet and wake flow /
- induced velocity /
- wake vortex models /
- jet flow models /
- CFD

HTML全文

图 1 飞机翼尖涡

Figure 1. Wing tip vortex of aircraft

下载: 全尺寸图片幻灯片

图 2 尾涡对飞机飞行的影响

Figure 2. The impact of wake vortex on flight

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图 3 涡诱导速度计算图

Figure 3. Vortex induced velocity computation figure

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图 4 喷流模型

Figure 4. Jet flow model

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图 5 计算域示意图

Figure 5. Computational domain schematic diagram

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图 6 飞机尾后涡线图

Figure 6. Vortex line figure after the tail of aircraft

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图 7 尾喷口计算域示意图

Figure 7. Jet nozzle computational domain schematic diagram

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图 8 尾喷流速度分布图

Figure 8. Jet flow velocity distribution diagram

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图 9 飞机尾后10 m处尾流场诱导速度

Figure 9. Induced velocity at 10 m after the tail of aircraft

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图 10 飞机尾后100 m处尾流场诱导速度

Figure 10. Induced velocity at 100 m after the tail of aircraft

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图 11 飞机尾后10 m对比结果

Figure 11. The comparison results at 10 m after the tail of aircraft

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图 12 飞机尾后100 m对比结果

Figure 12. The comparison results at 100 m after the tail of aircraft

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图 13 发动机喷流速度CFD计算结果

Figure 13. Jet flow velocity distribution computed via CFD

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图 14 喷流模型计算结果

Figure 14. Jet flow models computation results

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