Onset of vortex breakdown above a pitching delta wing
Onset of vortex breakdown above a pitching delta wing
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DOI：
10.2514/3.12145
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发表时间：
1994-08
期刊：
影响因子：
2.5
通讯作者：
M. Visbal
中科院分区：
文献类型：
--
作者：
M. Visbal
给出了大迎角俯仰保持机动下三角翼上方瞬态涡击穿的计算结果。采用隐式光束升温算法在移动网格上求解全三维Navier-Stokes方程，模拟了流动。对数值分辨率影响的评估以及与实验数据的良好比较表明，计算方法捕捉了瞬态击穿开始和初始阶段的基本动力学。沿涡轴的压力梯度对击穿起主导作用
Computational results are presented for transient vortex breakdown above a delta wing subject to a pitch-and-hold maneuver to high angle of attack. The flows are simulated by solving the full three-dimensional Navier-Stokes equations on a moving grid using the implicit Beam-Warming algorithm. An assessment of the effects of numerical resolution and favorable comparison with experimental data suggest the computational approach captures the basic dynamics of the onset and initial stages of transient breakdown. The pressure gradient along the vortex axis is found to play a dominant role in the initiation of breakdown