摘要
前缘缝翼尾流与主翼边界层混合的改变对主翼气动力具有重要影响。利用数值模拟手段,通过在前缘缝翼尾缘添加一定动量系数的喷流,改变前缘缝翼尾缘的尾流,进而改变尾流与主翼边界层的混合状况。求解二维多段翼模型30P30N在各个不同喷流条件下的二维非定常流场,结果表明:提高前缘缝翼尾缘喷流的动量系数,将使前缘缝翼尾流和主翼边界层混合开始点后移,提高主翼上表面负压峰值和主翼升力;混合开始点对主翼的负压峰值及升力均有一定的影响;增大来流攻角会抑制前缘缝翼尾流和主翼边界层的混合。
The influence of confluent boundary layer changing on aerodynamic force of the main element of multielement airfoils is significant.In order to alter the mixing condition of slat wake and main element boundary layer,slat wake varies with different momentum coefficients jet which applied at the trailing edge of slat.Numerical computation is used for solving two dimensional unsteady flow of multi-element airfoils model 30P30 Nat different jet momentum coefficients.The numerical results indicate that：the onset location of the mixed flow by slat wake and main element boundary layer moves downstream along main element chordwise direction with the jet momentum coefficient increased,the suction peak of main element on upper surface is improved,and the main element lift is enhanced.Onset location of mixing has effect on suction peak and lift of main element.The mixing flow of slat wake and main element boundary layer is restrained by the increasing of the angle of attack.
出处
《航空工程进展》
CSCD
2016年第1期30-37,共8页
Advances in Aeronautical Science and Engineering
关键词
多段翼
前缘缝翼尾流
边界层
动量系数
喷流
混合开始点
multi-element airfoils
slat wake
boundary layer
momentum coefficient
jet
onset location of mixing
