Direct numerical simulation of supersonic turbulent boundary layer subjected to a curved compression ramp
Direct numerical simulation of supersonic turbulent boundary layer subjected to a curved compression ramp
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DOI：
10.1063/1.4996762
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发表时间：
2017-12
影响因子：
4.6
通讯作者：
Fu-lin Tong;Xinliang Li;Yanhui Duan;Changping Yu
中科院分区：
文献类型：
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作者：
Fu-lin Tong;Xinliang Li;Yanhui Duan;Changping Yu
使用直接数值模拟对纵向弯曲压缩坡道上的超音速湍流边界层进行数值研究，自由流马赫数 M∞ = 2.9 和雷诺数 Reθ = 2300。总转角为 24°，凹曲率半径为传入湍流边界层厚度的 15 倍。在选定的条件下，由于逆压梯度较弱，激波足转移到压缩波扇形。曲线斜坡中的时间平均流场是统计附着的，其中瞬时流场接近间歇性瞬时分离状态。对相干涡结构的研究表明，当凹曲率沿翼展方向对齐时，大尺度涡包会显着增强。与之前的实验结果一致，发现凹曲率对平均速度剖面的对数区域的影响很小。激烈的...
Numerical investigations on a supersonic turbulent boundary layer over a longitudinal curved compression ramp are conducted using direct numerical simulation for a free stream Mach number M∞ = 2.9 and Reynolds number Reθ = 2300. The total turning angle is 24°, and the concave curvature radius is 15 times the thickness of the incoming turbulent boundary layer. Under the selected conditions, the shock foot is transferred to a fan of the compression wave because of the weaker adverse pressure gradient. The time-averaged flow-field in the curved ramp is statistically attached where the instantaneous flow-field is close to the intermittent transitory detachment state. Studies on coherent vortex structures have shown that large-scale vortex packets are enhanced significantly when the concave curvature is aligned in the spanwise direction. Consistent with findings of previous experiments, the effect of the concave curvature on the logarithmic region of the mean velocity profiles is found to be small. The intensi...