攻角变化对超音速进气道再起动特性的影响  

Effect of variation of angle of attack on restart behavior of supersonic inlet

作　　者：赵湘恒[1] 夏智勋[1] 方传波[1] 胡建新[1] 王德全[1] 游进[1] 

机构地区：[1]国防科技大学航天与材料工程学院,长沙410073

出　　处：《固体火箭技术》2011年第3期290-294,共5页Journal of Solid Rocket Technology

摘　　要：以二维非定常可压缩流的N-S方程为控制方程,采用SST k-ω湍流模型对攻角变化引起的超音速进气道再起动过程进行了数值模拟,研究了攻角变化对超音速进气道再起动特性的影响。结果表明,当超音速进气道不起动时,可通过合理改变攻角实现进气道的再起动工作;超音速进气道的再起动攻角随攻角变化速率的增大近似呈线性增加;攻角变化速率较大时,非稳态与稳态工况下相同攻角对应的超音速进气道性能差别较大。In order to study the effect of variation of angle of attack on restart behavior of the supersonic inlet,the unsteady restarting process of the supersonic inlet response to variation of angle of attack was simulated with two-dimensional unsteady compressible N-S equations and SSTk-ω turbulence model.The results show that the supersonic inlet at unstart can acheive restart by changing the angle of attack properly,and the value of the restart angle of attack tends to increase linearly with the change rate of the angle of attack,and performance differences of the supersonic inlet between steady and unsteady cases at the same angle of attack are more apparent at a high change rate of the angle of attack.

关 键 词：超音速进气道 攻角变化 再起动特性 非稳态 

分 类 号：V430[航空宇航科学与技术—航空宇航推进理论与工程]