文档介绍：
第 28 卷
第 5 期空气动力学学报 V o l. 28, N o. 5
2010 年 10 月 ACTA AERODYNAMICA SINICA Oct. , 2010
文章编号: 0258
1825( 2010) 05
0495
08
Experimental investigation of cross
flow instability
in swept
wing boundary layers
ZUO Sui
han, YANG Yong, LI Do ng , LI Yue
li
( N ational Key Labo ratory of Aerodynamic Design and Research, N orthw estern
Polytechnical U niversity, Xi
an
710072, China)
Abstract: Statio nary cross
flow instabilities and transition pattern in the boundary layer of a 45
swept w ing with and without
3D artificial leading edge roug hness w ere investigated by sublimation method. For the model without artificial roughness,
straight transition lines behind the minimum pressure point which are dominated by T
S instabilities appeared in the Reyn
o lds number rang e of 5. 50 105 ~ 1. 65 106 . When Re!1. 38 106 , t races of the most amplified stationary cro ss
flow
waves were detected, and 3. 5~ 4. 0mm spacing stripes agreed quite well w ith the results of linear stability theory . T he ex
treme sensitiv ity of the stationary disturbance to leading edge roug hness is verified at Re= 1. 65 106 . In order to mo dify
the most amplified cross
flow waves which usually dominate transition on the swept wing of an aircraft, different spacing
leading edge roughness w ere applied. At Re= 1. 38 106, 2. 5mm spacing roughness suppressed the most amplified