Investigations of High-Speed Civil Transport Inlet Unstart at Angle of Attack
Investigations of High-Speed Civil Transport Inlet Unstart at Angle of Attack
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DOI：
10.2514/2.2404
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发表时间：
1998-11
影响因子：
2.2
通讯作者：
Gecheng Zha;D. Knight;Donald Smith
中科院分区：
文献类型：
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作者：
Gecheng Zha;D. Knight;Donald Smith
使用三维时间精确的纳维-斯托克斯求解器对高速民用运输混合压缩轴对称入口在马赫数和 2 度攻角下的未启动瞬态进行了数值研究。采用鲍德温-洛马克斯代数湍流模型和槽泄放的外推均匀质量泄放边界条件。可以看出，当施加攻角时，背风侧的气流比零攻角时具有更强的压缩力。强压缩降低了末端激波上游的马赫数，因此使激波首先在背风侧向上游移动。初始激波运动从终端激波的分叉开始。由于中心体排气，分体式减震器的下部是稳定的，而减震器的顶部则继续向上游移动。当背风侧的末端激波通过泄气区域时，入口中心体肩部的激波/边界层相互作用引起分离，并且整个入口停止启动。总体计算的电场现象与实验观察结果定性一致。
The unstart transient of a high-speed civil transport mixed compression axisymmetric inlet at Mach 2 and 2-deg angle of attack was investigated numerically by using a three-dimensional time-accurate Navier‐Stokes solver. The Baldwin ‐Lomax algebraic turbulence model and an extrapolation uniform mass bleed boundary condition for the slot bleed were employed. It is observed that, when an angle of attack is imposed, the e ow on the leeward side has a stronger compression than that at zero angle of attack. The strong compression reduces the Mach number upstream of the terminal shock and therefore makes the shock move upstream e rst on the leeward side. The initial shock motion starts with the bifurcation of the terminal shock. The lower part of the split shock is stable because of the centerbody bleed, whereas the top part of the shock continues to travel upstream. When the terminal shock on the leeward side passes the bleed region, a separation is induced by the shock /boundary-layer interaction on the shoulder of the inlet centerbody, and the entire inlet is brought to unstart. The overall computed e owe eld phenomena agree qualitatively with the experimental observations.