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机译:用于垂直轴风力涡轮机的Naca 0012机翼上层流到湍流边界层过渡的数值研究
Department of Mechanical Engineering - University of Padova Via Venezia, I -35131 Padova, Italy;
Department of Mechanical Engineering - University of Padova Via Venezia, I -35131 Padova, Italy;
Department of Mechanical Engineering - University of Padova Via Venezia, I -35131 Padova, Italy;
cmm: blade chord; C_D -: airfoil total drag coefficient; C_(D,Pressure)- : airfoil total pressure drag coefficient; C_(D,skin)-: airfoil total skin friction drag coefficient; c_f-: airfoil local skin friction coefficient et al;
机译:偏心网格法在固定和振荡NACA0012机翼上的湍流流动的数值研究
机译:对用于城市环境中小型风力涡轮机的E387,S823,NACA 0012和NACA 4412机翼产生噪声的研究
机译:锯齿形壁对NACA0012机翼冲击波/边界层相互作用的被动控制数值评估
机译:使用移动表面边界层控制(MSBC)在Naca 0012翼型上的减阻的数值研究
机译:6马赫圆锥边界层内层流湍流的数值研究
机译:鱼的边界层控制:虹鳟在湍流中游荡的不稳定层流边界层
机译:6马赫锥边界层内层流-湍流过渡的数值研究
机译:NaCa 64a010翼型上区域吸力对层流边界层影响的初步风洞调查