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为了提高旋翼计算流体力学(CFD)流场计算效率及克服其在尾迹捕捉上的不足,将旋翼黏性涡粒子方法(VPM)与CFD分析相结合,建立了一个新的旋翼VPM/CFD耦合气动分析模型。在该模型中,采用VPM分析以实现对旋翼尾迹中黏性涡的高效捕捉而不引入数值耗散,而采用CFD分析用于精确地模拟旋翼桨叶近体区域内复杂的流动现象,同时也为VPM分析提供一个较高精度的涡源模型。至于两者信息交换,则使用集中涡源法将CFD信息传递至VPM分析,而VPM计算得到的尾迹信息则通过边界修正施加至CFD域的远场边界上,从而可以鲁棒地实现CFD域与VPM域的耦合计算。在此基础上,对“Helishape 7A旋翼”小前进比前飞桨-涡干扰(BVI)状态进行了较为深入的气动分析,计算结果表明:与全CFD计算比较,建立的VPM/CFD耦合分析模型可以有效地避免旋翼尾迹区桨尖涡的数值耗散,从而更加可靠地捕捉桨-涡干扰状态下的桨叶非定常气动载荷脉动,同时对于本文算例,计算效率可以提高30%以上。
In order to improve computational fluid dynamics computational fluid dynamics (CFD) flow field computational efficiency and overcome its shortcomings in wake catching, a new rotor VPM / CFD aerodynamic coupling was established by combining rotor viscous vortex particle method (VPM) with CFD analysis Analysis model. In this model, VPM analysis is used to achieve efficient capture of viscous vortices in the rotor wake without introducing numerical dissipation, whereas CFD analysis is used to accurately model the complex flow phenomena in the vicinity of the rotor blades, It provides a more accurate vortex source model for VPM analysis. As for the information exchange between the two, the CFD information is transmitted to the VPM analysis using the centralized vortex method, and the wake information calculated by the VPM is applied to the far-field boundary of the CFD domain through the boundary correction so that the CFD domain and VPM domain coupling calculation. On this basis, a more in-depth aerodynamic analysis was conducted on the “Helishape 7A rotor” small forward forward flight propeller-vortex disturbance (BVI) condition. The calculated results show that compared with the full CFD calculation, the established VPM / CFD coupling The analytical model can effectively avoid the numerical dissipation of the tip vortex of the rotor wake area, so as to more reliably capture the unsteady aerodynamic load pulsation of the blade under the propeller-vortex interference condition. Meanwhile, the computational efficiency can be improved by more than 30% .