摘要
风洞测力实验结果表明 ,本文所采用的沟槽面设计均能在一定的迎角范围内减少三角翼的阻力。在迎角α >2 0°、侧滑角 β =0°～ 30°的范围内可使阻力系数降低 2 .5 % ,而几乎与侧滑角无关。另外 ,h =s =0 .2mm的“V”型沟槽表面在α =6°时减阻效果最佳 ,减阻量为4 0 % ;相应的升阻比亦最大 ,约增加 61%。
The wind tunnel experiments indicated that the delta wing with riblets surfaces can reduce its drag coefficient at certain extent of angle of attack( α ). When α is greater than 20° and the angle of slide β is in the range of 0° to 30°, nearly in spite of β , the drag coefficients can be reduced by 2.5%. For the 'V' shaped riblets surfaces with h=s =0.2mm, a maximum reduction of drag coefficient 40% has been obtained at α =6°,and the increment of the lift to drag ratio also reaches a maximum value of 61%.
出处
《空气动力学学报》
CSCD
北大核心
2001年第3期283-287,共5页
Acta Aerodynamica Sinica
基金
国家部委级基金资助项目 (13.3.1 6 ) .
