论文标题
使用分离剪切层固定湍流模型对冰翼的数值模拟
Numerical Simulation of Iced Wing Using Separating Shear Layer Fixed Turbulence Models
论文作者
论文摘要
使用雷诺平均的Navier-Stokes方法研究了对机翼和机翼上釉面冰的空气动力学预测。考虑到湍流的非平衡特性，开发了两个分离固定的湍流模型。关键的临时修复是湍流产量与耗散的局部比率的术语，该术语用于扩增ω-方程的破坏项，以增加全湍流区域的分离剪切层中的涡流粘度。当湍流正在开发时，采用剪切应力限制器来适当模拟剪切层转变的开始过程。提出的分离固定术语可以轻松地实现到当前求解器中。使用修改模型对两个机翼和一个带有冰积聚的三维扫描机翼进行了数值测试。结果表明，分离的剪切层固定可以提高模型在大量攻击角度预测失速行为方面的能力。模拟的平均流场和湍流强度分布与实验数据一致。
Aerodynamic prediction of glaze ice accretion on airfoils and wing is studied using the Reynolds-averaged Navier-Stokes method. Two separation fixed turbulence models are developed considering the nonequilibrium characteristics of turbulence. The key ad hoc fix is a term of the local ratio of turbulent production to dissipation, which is used to amplify the destruction term of the ω-equation to increase the eddy viscosity in a separating shear layer of the fully turbulent region. A shear stress limiter is adopted to appropriately simulate the beginning process of the shear layer transition when the turbulence is under development. The proposed separation fixed terms can be easily implemented into current solvers. Two airfoils and a three-dimensional swept wing with ice accretions are numerically tested using the modified models. The results indicate that the separating shear layer fixes improve the ability of the models in predicting the stall behavior at large angles of attack. The simulated averaged flow field and turbulence intensity distribution are consistent with experimental data.
