摘要
通过ANSYS FLUENT,基于湍流涡粘模型中的S-A模型、k-ωSST模型和Realizable k-ε模型对NACA0012机翼的尾涡流场进行数值模拟,采用Boussinesq估算法提取了雷诺应力,对比分析了3种模型数值计算。结果发现:Realizable k-ε模型能很好地模拟涡核处的湍动能和湍涡粘性;S-A模型不能用于模拟雷诺正应力,Realizable k-ε和k-ωSST模型模拟涡核处的雷诺正应力的变化取决于涡核处湍动能的变化情况;S-A模型模拟出在涡核附近雷诺切应力存在正负波瓣,而Realizable k-ε和k-ωSST模型在涡核处几乎不存在雷诺切应力值。
Based on turbulent eddy viscosity models： S- A model, k-to ~＇1＇ model and tteatlzaDle r- 6 model,numerical simulations of the NACAO012 wing＇s wake vortex field were done by ANSYS FLUENT. Boussinesq estimation method was used to extracte the Reynolds stress. Comparing three models, results shown as following statement： Realizable k-8 model holds the excellent ability to simulate the turbulent kinetic energy and turbulent viscosity at the vortex cores. The S- A model is not suitable to simulate the Reynolds positive stress. The changes of Reynolds positive stress depend on the variation of turbulent kinetic energy at the vortex cores, which were done via Realizable k- ε and k- ω SST models. The existence of positive and negative lobe of Reynolds stress in the vicinity of the eddy cores was simulated in the S- A model,whereas the Reynolds stress value is almost absent in the simulation of Realizable k- ε and k-ω SST models.
出处
《航空计算技术》
2017年第6期65-68,共4页
Aeronautical Computing Technique
基金
国家自然科学基金与中国民航基金联合项目资助(U1633109
U1533116)
中央高校基本科研业务经费专项资金项目资助(3122014B005)
中国民航大学大学生创新创业训练计划项目资助(201710059054)
关键词
翼尖涡
数值模拟
湍流模型
涡核
雷诺应力
wing tip vortex
numerical simulation
turbulence model
vortex cores
Reynolds stress
