逆向射流对高超声速升力体构型的减阻特性研究
Study on the Drag Reduction Characteristics of Opposing Jet on Hypersonic Lifting Body Configuration
王林 1王宇楠 1罗振兵 1周岩 1谢玮 1刘强1
作者信息
- 1. 国防科技大学空天科学学院,长沙 410073
- 折叠
摘要
在高超声速飞行过程中,飞行器往往会面临巨大的阻力,严重限制了其飞行性能,并增加了飞行器表面的热负荷和材料应力.针对这一问题,通过数值模拟系统地分析了射流孔数量、位置和攻角对升力体减阻性能的影响.研究结果表明,随着射流孔数量的增加,整体减阻率显著提高,有效降低了升力体头部的高压区域,但也导致四周流场的不稳定性增强.射流孔位置对激波脱体距离和"气膜"厚度具有重要影响.此外,增大攻角会导致整体减阻率下降,但对局部减阻率影响较小,同时会增加上下壁面之间的压差.进一步比较研究发现,在20 km和55 km高空条件下,这3种因素对减阻性能的影响规律保持一致.研究结果为设计高效减阻方案提供了重要参考.
Abstract
During hypersonic flight,aircraft often face significant drag,which severely limits their flight performance and increases the thermal load and material stress on the aircraft surface.To address this issue,the effects of the number,location,and angle of attack of jet orifices on the lift-to-drag performance of the lifting body are systematically analyzed through numerical simulations.The results indicate that an increased number of jet holes leads to a significant improvement in overall drag reduction,effectively reducing the high-pressure region at the head of the lifting body.However,it also induces instability in the surrounding flow field.The position of the jet hole plays a crucial role in determining the shock wave detachment distance and boundary layer thickness.Moreover,an increase in the angle of attack causes a decrease in overall drag reduction while having minimal impact on local drag reduction,resulting in an increased pressure difference between the upper and lower surfaces.Furthermore,comparative analysis reveals consistent trends in the effects of these three factors on drag reduction performance under high-altitude conditions at 20 km and 55 km.The research findings provide valuable insights for the design of efficient drag reduction schemes.
关键词
逆向射流/减阻/升力体/高超声速飞行器/激波Key words
Opposing jet/Drag reduction/Lifting body/Hypersonic vehicle/Shock wave引用本文复制引用
基金项目
国家科技重大专项(J2019-Ⅲ-0010-0054)
国家自然科学基金(12202488)
国家自然科学基金(92271110)
出版年
2024
NETL
NSTL
万方数据