Aerodynamic Calculation of Airfoil Dynamic Stall Based on Data-Driven Transition Model
-
摘要:
低Reynolds数下层流分离和分离诱导转捩现象复杂,数值仿真难度大。基于全连接反向传播神经网络,建立了低Reynolds数转捩间歇因子的数据驱动模型,通过优化设计选择了能够反映转捩过程的数据驱动模型的流场输入参数,辨识了转捩间歇因子,据此修正了k-ω SST二方程湍流模型,求解二维翼型动态失速下的流场演化和非定常气动力特性。结果表明,数据驱动的转捩方程耦合二方程湍流模型具有一定的迎角泛化能力,能够反映动态失速下前缘涡增长与脱落、流动再附着等典型流动状态。基于数据驱动转捩模型的动态失速下非定常气动升力预测结果与基于SST-γ三方程模型的CFD计算结果相比,相对误差小于12%。
Abstract:The laminar flow separation and separation-induced transition at low Reynolds number are complex, and have great difficulty in numerical simulation. Based on fully-connected back-propagation neural network, a data-driven model of intermittency at low Reynolds number was established. The input parameters of the data-driven model to reflect transition process and predict intermittency were selected through optimization design. By modifying the k-ω SST two equation turbulence model with a data-driven transition equation, the flow field evolution and unsteady aerodynamic characteristics of a two-dimensional airfoil under dynamic stall were solved. Results show that the data-driven transition equation combined with two equation turbulence model has the generalization ability for the angle of attack, and clearly reflects the typical flow conditions such as the growth and shedding of the leading-edge vortex and the reattachment of the flow under dynamic stall. The relative error of unsteady aerodynamic lift in dynamic stall between the data-driven transition model and the SST-γ three equation model is lower than 12%.
-
Key words:
- turbulence model /
- flow transition /
- data-driven /
- neural network /
- dynamic stall
-
表 1 T3A平板入口条件
Table 1. Inlet conditions of T3A flat plate
U∞/(m/s) Tu∞/(%) Rμ ReL k ω 5.4 3.35 11.5 6.12×105 0.047 6 264.63 表 2 神经网络训练集与测试集迎角设置
Table 2. Angle of attack setting of training and testing datasets
αT/(°) αP/(°) 4,8 2,4,5,6,7,8 -
[1] 张健, 张德虎. 高空长航时太阳能无人机总体设计要点分析[J]. 航空学报, 2016, 37(S1): S1-S7.Zhang J, Zhang D H. Essentials of configuration design of HALE solar-powered UAVs[J]. Acta Aeronautica et Astronautica Sinica, 2016, 37(S1): S1-S7(in Chinese). [2] Barnes C J, Visbal M R. Stiffness effects on laminar se-paration flutter[J]. Journal of Fluids and Structures, 2019, 91: 102767. doi: 10.1016/j.jfluidstructs.2019.102767 [3] McCroskey W J, Carr L W, McAlister K W. Dynamic stall experiments on oscillating airfoils[J]. AIAA Journal, 1976, 14(1): 57-63. doi: 10.2514/3.61332 [4] Sheng W, Galbraith R A, Coton F N. Prediction of dynamic stall onset for oscillatory low-speed airfoils[J]. Journal of Fluids Engineering, 2008, 130(10): 101204. doi: 10.1115/1.2969450 [5] Wu Y, Dai Y T, Yang C, et al. Effect of trailing-edge morphing on flow characteristics around a pitching airfoil[J]. AIAA Journal, 2023, 61(1): 160-173. doi: 10.2514/1.J061055 [6] Spentzos A, Barakos G, Badcock K, et al. Investigation of three-dimensional dynamic stall using computational fluid dynamics[J]. AIAA Journal, 2005, 43(5): 1023-1033. doi: 10.2514/1.8830 [7] Wang S Y, Ingham D B, Ma L, et al. Turbulence modeling of deep dynamic stall at relatively low Reynolds number[J]. Journal of Fluids and Structures, 2012, 33: 191-209. doi: 10.1016/j.jfluidstructs.2012.04.011 [8] Kim Y, Xie Z T. Modelling the effect of freestream turbulence on dynamic stall of wind turbine blades[J]. Computers & Fluids, 2016, 129: 53-66. [9] Menter F R. Two-equation eddy-viscosity turbulence models for engineering applications[J]. AIAA Journal, 1994, 32(8): 1598-1605. doi: 10.2514/3.12149 [10] Van Ingen J L. The eN method for transition prediction. Historical review of work at TU Delft[R]. AIAA 2008-3830, 2008: 3830. [11] 朱震, 宋文萍, 韩忠华. 基于双eN方法的翼身组合体流动转捩自动判断[J]. 航空学报, 2018, 39(2): 123-134.Zhu Z, Song W P, Han Z H. Automatic transition prediction for wing-body configuration using dual eN method[J]. Acta Aeronautica et Astronautica Sinica, 2018, 39(2): 123-134(in Chinese). [12] 韩忠华, 王绍楠, 韩莉, 等. 一种基于动模态分解的翼型流动转捩预测新方法[J]. 航空学报, 2017, 38(1): 30-46.Han Z H, Wang S N, Han L, et al. A novel method for automatic transition prediction for flows over airfoils based on dynamic mode decomposition[J]. Acta Aeronautica et Astronautica Sinica, 2017, 38(1): 30-46(in Chinese). [13] Launder B E, Sharma B I. Application of the energy-dissipation model of turbulence to the calculation of flow near a spinning disc[J]. Letters in Heat and Mass Transfer, 1974, 1(2): 131-137. doi: 10.1016/0094-4548(74)90150-7 [14] Menter F R, Langtry R, Völker S. Transition modelling for general purpose CFD codes[J]. Flow, Turbulence and Combustion, 2006, 77(1/4): 277-303. [15] Lodefier K, Merci B, De Langhe C, et al. Transition modelling with the SST turbulence model and an intermittency transport equation[C]. ASME Turbo Expo 2003, Collocated with the 2003 International Joint Power Gene-ration Conference. Atlanta, Georgia, USA: ASME, 2003: 771-777. [16] Wang L, Fu S. Development of an intermittency equation for the modeling of the supersonic/hypersonic boundary layer flow transition[J]. Flow, Turbulence and Combustion, 2011, 87(1): 165-187. doi: 10.1007/s10494-011-9336-1 [17] Fu S, Wang L. RANS modeling of high-speed aerodynamic flow transition with consideration of stability theory[J]. Progress in Aerospace Sciences, 2013, 58: 36-59. doi: 10.1016/j.paerosci.2012.08.004 [18] Xu J K, Bai J Q, Fu Z Y, et al. Parallel compatible transition closure model for high-speed transitional flow[J]. AIAA Journal, 2017, 55(9): 3040-3050. doi: 10.2514/1.J055711 [19] Dhawan S, Narasimha R. Some properties of boundary layer flow during the transition from laminar to turbulent motion[J]. Journal of Fluid Mechanics, 1958, 3(4): 418-436. doi: 10.1017/S0022112058000094 [20] Suzen Y B, Huang P G. Modeling of flow transition using an intermittency transport equation[J]. Journal of Fluids Engineering, 2000, 122(2): 273-284. doi: 10.1115/1.483255 [21] Cho J R, Chung M K. A k-ε-γ equation turbulence model[J]. Journal of Fluid Mechanics, 1992, 237: 301-322. doi: 10.1017/S0022112092003422 [22] Steelant J, Dick E. Modelling of bypass transition with conditioned Navier-Stokes equations coupled to an intermittency transport equation[J]. International Journal for Numerical Methods in Fluids, 1996, 23(3): 193-220. doi: 10.1002/(SICI)1097-0363(19960815)23:3<193::AID-FLD415>3.0.CO;2-2 [23] Menter F R, Smirnov P E, Liu T, et al. A one-equation local correlation-based transition model[J]. Flow, Turbulence and Combustion, 2015, 95(4): 583-619. doi: 10.1007/s10494-015-9622-4 [24] Singh A P, Duraisamy K. Using field inversion to quantify functional errors in turbulence closures[J]. Physics of Fluids, 2016, 28(4): 045110. doi: 10.1063/1.4947045 [25] Singh A P, Medida S, Duraisamy K. Machine-learning-augmented predictive modeling of turbulent separated flows over airfoils[J]. AIAA Journal, 2017, 55(7): 2215-2227. doi: 10.2514/1.J055595 [26] Yang M C, Xiao Z X. Improving the k-ω-γ-Ar transition model by the field inversion and machine learning framework[J]. Physics of Fluids, 2020, 32(6): 064101. doi: 10.1063/5.0008493 [27] Zafar M I, Xiao H, Choudhari M M, et al. Convolutional neural network for transition modeling based on linear stability theory[J]. Physical Review Fluids, 2020, 5(11): 113903. doi: 10.1103/PhysRevFluids.5.113903 [28] Ott J, Pritchard M, Best N, et al. A Fortran-Keras deep learning bridge for scientific computing[J]. Scientific Programming, 2020, 2020: 8888811. [29] Maulik R, Sharma H, Patel S, et al. Deploying deep learning in OpenFOAM with TensorFlow[R]. AIAA 2021-1485, 2021: 1485. [30] Maulik R, Sharma H, Patel S, et al. A turbulent eddy-viscosity surrogate modeling framework for Reynolds-ave-raged Navier-Stokes simulations[J]. Computers & Fluids, 2021, 227: 104777. [31] Suluksna K, Juntasaro E. Assessment of intermittency transport equations for modeling transition in boundary layers subjected to freestream turbulence[J]. International Journal of Heat and Fluid Flow, 2008, 29(1): 48-61. doi: 10.1016/j.ijheatfluidflow.2007.08.003 [32] Lee T, Gerontakos P. Investigation of flow over an oscillating airfoil[J]. Journal of Fluid Mechanics, 2004, 512: 313-341.