The process of vortex shedding from an impulsively started wing of an aircraft is simulated numerically.

本项目数值模拟了机翼突然起动涡旋脱落过程.

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It is showed that allowing for effect, spectrum width of vortex shedding signal experiences considerable changes.

研究表明,考虑热效应后的旋涡脱落发生明显变化, 表现在旋涡脱落信号傅里叶变换峰宽的改变.

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Such parameters of flow characteristics are investigated as lift and drag coefficient and vortex shedding frequencies.

计算了圆柱的升阻力系数、尾涡脱落频率等描述绕流问题的主要参量.

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