典型及衍生激波针构型的减阻降热流动特性
Flow characteristics of drag and heat reduction of typical and derived aero-spikes configuration
何坤 1袁化成2
作者信息
- 1. 南京航空航天大学能源与动力学院,南京 210016;北京航空航天大学航空发动机研究院,北京 102206
- 2. 南京航空航天大学能源与动力学院,南京 210016
- 折叠
摘要
为探索激波针对超声速钝头飞行器进行减阻降热时的更优衍生构型,采用数值模拟方法对3种典型单扰流物构型、6种双扰流物构型、两类多扰流物构型和钝锥型激波针的流动特性进行了研究,认为加装激波针后的几何本质相当于"镂空式"的锥型钝头体.模拟结果显示:激波针头部扰流物相对直径较大时,减阻率随激波针相对长度的变化曲线没有明显的峰值点,而是存在一个变动幅度很小的峰值段,且相对直径在0.3～0.4左右时减阻效果最佳;典型激波针的最大减阻率约为50％,采用双扰流物构型时略有提升;中部增加多个扰流物时减阻率随扰流物数量增多而增大,最大减阻率超过60％,但气动加热问题较严重.相比而言,钝锥型激波针减阻降温的综合性能最好,最大减阻率可达60％左右,降温率约为7％.
Abstract
In order to explore a better derived configuration of the aero-spike for drag and heat reduction of the supersonic blunt aircraft,numerical simulation was used to study the flow characteristics of three kinds of typical configurations with single flow interferent,six kinds of configurations with double flow interferents,two types of configurations with multiple flow interferents and blunted cone-spike;it was believed that the geometric essence of adding an aero-spike was equivalent to a"hollowed-out"conical blunt body.The simulation results showed that when the relative diameter of the flow interferent at the head was large,the variation curve of drag reduction rate with the relative length of the spike didn't have an obvious peak point,instead,there was a peak stage with very little variation,and the drag reduction effect was best when the relative diameter was about 0.3-0.4;the maximum drag reduction rates of the typical spikes were about 50％and slightly increased by using configurations with double flow interferents;when multiple flow interferents were added in the middle,the drag reduction rates increased with the growing number of flow interferents,the maximums were more than 60％,but the aerodynamic heating problem was more serious.In comparison,the blunted cone-spike had the best comprehensive performances of drag and heat reduction,its maximum drag reduction rate could reach about 60％,and the heat reduction rate was about 7％.
关键词
激波针/衍生构型/超声速/减阻降热/流动特性Key words
aero-spike/derived configuration/supersonic/drag and heat reduction/flow characteristics引用本文复制引用
出版年
2024
NETL
NSTL
万方数据