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。
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.
作者
杨立波
丛岩
YANG Libo;CONG Yan(Guangdong University of Science and Technology,Dongguan 523083,China;Air Force Aviation University,Changchun 130013,China)
出处
《红外技术》
CSCD
北大核心
2021年第10期940-948,共9页
Infrared Technology
基金
东莞市社会科技发展(一般)项目(2019507154529)。
关键词
尾喷流
诱导速度
尾涡模型
喷流模型
CFD
jet and wake flow
induced velocity
wake vortex models
jet flow models
CFD
