摘要
使用Fluent求解器,分别对超临界翼型上翼面全吸气及部分区域吸气时进行了层流减阻数值研究,探究了不同吸气系数及雷诺数对翼型转捩位置和阻力的影响规律.结果表明：①对上翼面全弦长范围进行吸气控制,能有效地推后转捩位置.当吸气系数超过某一值时,能够使上翼面达到全层流状态,从而减小翼型阻力;②只对上翼面15%65%弦长区域内进行吸气控制,当吸气系数达到一定值时,可达到与全吸气时几乎相同的减阻效果;③其他飞行条件相同时,在较小雷诺数下,减阻效果较好.
Numerical simulation of laminar and drag-reduction control was carried out on both full and partial upper region of a supercritical airfoil;furthermore,the effects of different suction coefficients and Reynold numbers on the transitional position and drag were studied by using the computational fluid dynamics code,Fluent.The results show that：（1） transitional position could be effectively delayed with the full suction control on the whole upper surface,and the upper surface could reach full laminar state when the suction coefficient exceeds some value,so the drag could be decreased.（2） When the suction control is only carried out on 15%65% of the upper surface,at a certain suction coefficient,the efficiency of drag-reduction is nearly the same as full suction control.（3） When other flight conditions are the same,the efficiency of drag-reduction is better at a lower Reynold number.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2010年第11期2443-2449,共7页
Journal of Aerospace Power
基金
国防预先研究项目(61901010201)
航空支撑基金(08ZA51003)
关键词
超临界翼型
吸气技术
层流控制
全吸气
数值模拟
减阻控制
supercritical airfoil； suction technology； laminar flow control； full suction； numerical simulation； drag-reduction control；
