Stability of Supersonic Swept-Wing Boundary Layers with or without Crossflow
Stability of Supersonic Swept-Wing Boundary Layers with or without Crossflow
复制标题
有或没有横流的超音速后掠翼边界层的稳定性
DOI：
10.2322/tjsass.48.193
复制
发表时间：
2006
影响因子：
1.1
通讯作者：
T. Nomura
中科院分区：
文献类型：
--
作者：
T. Nomura
本文研究了由NAL超音速实验飞机的半翼展模型制成的无限后掠机翼上的三维超音速边界层的稳定性。原机翼的设计是为了抑制巡航条件下的流向和横流不稳定性。通过对全边界层和无横流边界层的线性稳定性分析，证实了全边界层中第一模态波的空间增长主要是由于流向不稳定性引起的，并在设计攻角附近受到限制。
We examine the stability of three-dimensional supersonic boundary layers over an infinite swept wing made from the semispan model of the NAL supersonic experimental airplane. The original wing was designed so as to suppress both streamwise and crossflow instabilities under cruise conditions. It is confirmed through linear stability analyses of the full boundary layer and the boundary layer without crossflow that the spatial growth of first-mode waves in the full boundary layer is mainly due to streamwise instability and restrained near the design angle of attack.