| 夏震昊,唐斌,于紫江.“Click”运动高升力机制[J].,2024,64(1):9-20 |
| “Click”运动高升力机制 |
| High lift mechanism of ″Click″ motion |
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| DOI：10.7511/dllgxb202401002 |
| 中文关键词: “Click”运动 计算流体力学 前缘涡 展向流动 |
| 英文关键词: ″Click″ motion computational fluid dynamics leading-edge vortex axial flow |
| 基金项目:国家自然科学基金资助项目(11202048). |
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| 中文摘要: |
| 研究了具有“Click”运动的模型翼在三维流场中的气动特性．采用计算流体力学方法求解三维非定常不可压缩Navier-Stokes方程，对比了简谐和“Click”运动所产生的升力与阻力，研究了升力最大时的前缘涡特性和展向流动．结果表明，在下拍过程的升力最大处，“Click”和简谐运动的前缘涡能够分别维持至翼展的80%和60%处．两种运动都会在翼展方向存在维持展向流动的压力梯度，而“Click”运动具有更显著的展向压力梯度，对展向涡度的能量输运效率更高，因此其前缘涡能够保持更完整的形态．在上拍过程中，两种运动的前缘涡形态差异不明显，“Click”运动快速上拍的运动特点使其能够快速地摆脱尾涡的干扰，从而维持升力． |
| 英文摘要: |
| The aerodynamic characteristics of a model wing with ″Click″ motion in a 3-dimensional (3-D) flow field are investigated. The 3-D unsteady incompressible Navier-Stokes equations are solved using computational fluid dynamics (CFD) method, and the lift and drag of the harmonic and ″Click″ motions are compared. The leading-edge vortex (LEV) characteristics and the axial flow are studied when the lift is maximum. The results show that the LEV of the ″Click″ and harmonic motions can be maintained up to 80% and 60% of the wingspan, respectively, at the maximum lift during the downstroke. Both motions have pressure gradients in the wingspan direction to keep the axial flow, and the ″Click″ motion has a more significant pressure gradient in the wingspan direction and is more efficient in the energy transport to the spreading vorticity, so its leading-edge vortex can maintain a more complete morphology. The morphological difference between the LEV of the two motions is not evident during the upstroke, and the fast upstroke motion characteristic of the ″Click″ motion can rapidly depress the disturbance of the wake vortex and thus maintain the lift. |
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