| 飞机翼身干扰流动分离机理研究 |
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| 引用本文： | 袁广田,黄鹏,韩意新.飞机翼身干扰流动分离机理研究[J].应用力学学报,2020(1):98-104,I0007. |
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| 作者姓名： | 袁广田 黄鹏 韩意新 |
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| 作者单位： | 中国飞行试验研究院飞机所 |
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| 摘 要： | 采用CFD(计算流体力学)方法,结合风洞试验结果,对飞机翼身干扰流动分离机理进行了研究。分析了机翼根部马蹄涡、边角涡的内部结构和形成过程;研究了机身和机翼的压力分布及附面层,进而总结给出了飞机翼根流动分离机理;同时也验证了CFD方法对翼身干扰计算的准确性。研究结果表明:机翼前缘对气流的阻挡作用形成较高的逆压梯度,使气流产生回流形成马蹄涡,马蹄涡影响翼根表面附面层,使机翼机身附面层掺混失稳,向下游流动发展形成边角涡。
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| 关 键 词： | 翼身干扰 流动分离 CFD 风洞试验 |
Mechanism of flow separation induced by aircraft wing-body interference |
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| Yuan Guangtian,Huang Peng,Han Yixin.Mechanism of flow separation induced by aircraft wing-body interference[J].Chinese Journal of Applied Mechanics,2020(1):98-104,I0007. |
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| Authors: | Yuan Guangtian Huang Peng Han Yixin |
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| Institution: | (Aircraft Flight Test Technology Institute,710089,Xi’an,China) |
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| Abstract: | The CFD(Computational Fluid Dynamics)technology and the wind tunnel test are used to study the flow separation phenomenon induced by wing-body interference.Inner structure and generation of horseshoe vortex and corner vortex are analyzed.Pressure contours and boundary layers on body and wing were studied.Finally,Mechanism of flow separation induced by aircraft wing-body interference is given,which verifies the accuracy of CFD technology to the wing-body interference.Results show that adverse pressure gradients form because of obstructing of leading edge of wing to flow.Horseshoe vortex forms because the gradients make flow go back.It mixes boundary layers at the wing root and results in them unsteady.Unsteady flow develops into corner vortex downstream. |
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| Keywords: | wing-body interference flow separation CFD wind tunnel test |
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