沉浮运动对翼型非定常气动力影响分析
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南京航空航天大学直升机动力学全国重点实验室

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V211.3

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江苏高校优势学科建设工程资助项目;南京航空航天大学科研与实践创新计划资助项目(xcxjh20210105)


Analysis on Impact of Plunging Motion on Airfoil Unsteady Aerodynamic Force
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National Key Laboratory of Helicopter Dynamics, Nanjing University of Aeronautics and Astronautics

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    摘要:

    采用计算流体力学的方法,建立了针对翼型动态失速数值模拟的数值计算模型,分析沉浮运动对翼型非定常气动力的影响。通过与NACA0012翼型的俯仰运动风洞实验数据进行比较,模型在轻度失速和深度失速状态下的模拟结果与试验值吻合较好,验证了本文数值计算模型的准确性和可行性。将NACA23012翼型的沉浮运动等效为俯仰运动,两种运动方式计算得到的翼型升力特性很接近,但力矩特性差异明显,随着沉浮幅值和来流马赫数的增大,力矩特性差异进一步扩大。增加沉浮幅值,俯仰和沉浮运动气动力矩的阻尼作用明显增强,增大来流马赫数,力矩阻尼作用减小,并在0.85马赫数状态下出现力矩发散现象。

    Abstract:

    A numerical calculation model for airfoil dynamic stall numerical simulation was established by computational fluid dynamics method, and the influence of plunging motion on airfoil unsteady aerodynamic force was analyzed. The simulation results were compared to the pitching motion wind tunnel experimental data of NACA0012 airfoil, and the results of the model under mild stall and deep stall conditions were in good agreement with the experimental values, which verified the accuracy and feasibility of the numerical calculation model. The plunging motion of NACA23012 airfoil was equivalent to the pitching motion, the lift characteristics of airfoil under the two motion modes are very close, but the moment characteristics are obviously different. With the increase of amplitude of plunging motion and inflow Mach number, the difference of moment characteristics is further expanded. With the increase of amplitude of plunging motion, the damping effect of aerodynamic moment of pitching and plunging motions is obviously enhanced, with the increase of inflow Mach number, the damping effect is reduced, and the moment divergence occurs at the state of 0.85 Mach number.

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彭裕,虞志浩. 沉浮运动对翼型非定常气动力影响分析[J]. 科学技术与工程, , ():

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  • 收稿日期:2024-04-23
  • 最后修改日期:2024-05-27
  • 录用日期:2024-06-05
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