Unsteady aerodynamic characterization computation and analysis of an airfoil based on TDDES model
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摘要:
针对旋翼翼型动态失速的模拟精度不高的问题，利用课题组发展的延迟分离涡（delay detached eddy simulation, DDES）模型与$ \gamma {\text{-}}\overline{{{Re}}_{\theta t}} $耦合模型（transitional delay detached eddy simulation, TDDES）进行非定常气动特性研究，该模型引入新的RANS（Reynolds-averaged Navier-Stokes equation）/LES（large eddy simulation）转换函数，减少了由LES模型的网格依赖性引起的不确定性。选取NACA0012和SC1095翼型进行非定常计算，并与URANS-SST（unsteady Reynolds-averaged Navier-Stokes with shear stress transport）和URANS-$ \gamma {\text{-}}\overline{{{Re}}_{\theta t}} $模型的计算结果进行对比，系统地验证了TDDES模型对非定常气动特性的模拟能力。研究结果表明：TDDES模型相对于URANS方法，能够更准确地预测升阻力系数迟滞回线及动态失速涡的演化规律，能够更准确地预测翼型的分离流动，同时保持了$ \gamma {\text{-}}\overline{{{Re}}_{\theta t}} $转捩模型较高的转捩预测精度和DDES模型对分离流动的模拟能力。
Abstract:To address the issue of poor simulation accuracy for the dynamic stall of rotor wing airfoils, this study employed the delay detached eddy simulation (DDES) model and the $ \gamma {\text{-}}\overline{{{Re}}_{\theta t}} $ coupled model (TDDES) models developed by the research group to investigate the unsteady aerodynamic characteristics. It introduced a new RANS(Reynolds-averaged Navier-Stokes equation)/LES (large eddy simulation)switching function to reduce the uncertainty caused by the grid-dependence of the LES model. Unsteady simulations were conducted on the NACA0012 and SC1095 airfoils. The results were compared with those from URANS-SST (unsteady Reynolds-averaged Navier-Stokes with shear stress transport) and URANS-$ \gamma {\text{-}}\overline{{{Re}}_{\theta t}} $ models to systematically verify the capability of the TDDES model in simulating unsteady aerodynamic characteristics. The results showed that, compared to URANS methods, the TDDES model achieved higher accuracy in predicting lift/drag coefficient hysteresis loops and the evolution of dynamic stall vortices, as well as the separation flow of the airfoil more accurately. Furthermore, it retained the higher transition prediction accuracy of the $ \gamma {\text{-}}\overline{{{Re}}_{\theta t}} $ transition model and the simulation capability of the DDES model for the separation flow.
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Key words:
- dynamic stall /
- unsteady transition /
- unsteady rotor simulation /
- TDDES model /
- separated flow
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图 4 SC1095翼型非定常气动力计算值与实验值对比
Figure 4. SC1095 airfoil comparison of unsteady aerodynamic calculated and experimental value
图 7 NACA0012翼型非定常气动力计算值与实验值对比
Figure 7. NACA0012 airfoil comparison of unsteady aerodynamic calculated and experimental values
图 9 SC1095翼型深失速非定常气动力计算值与实验值对比
Figure 9. SC1095 airfoil comparison of unsteady aerodynamic calculated and experimental values at deep stall
表 1 振荡翼型计算工况
Table 1. Computation condition for oscillating airfoils
参数 NACA0012翼型 SC1095翼型 轻失速 深失速 轻失速 深失速 Ma 0.600 0.283 0.302 0.279 Re/106 4.80 3.45 3.92 3.60 $ {\alpha }_{\mathrm{mean}} $/（°） 4.86 14.91 9.74 14.91 $ {\alpha }_{\mathrm{amp}} $/（°） 2.44 9.88 9.90 9.87 $ k $ 0.081 0.151 0.099 0.156 
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