用N－S方程计算翼型非定常粘性大攻角绕流  

Calculation for Unsteady Viscous Flows Around Airfoil with High Angle-Of-Attack Using Navier-Stokes Equations

作　　者：罗建国[1] 张建柏[1] 

机构地区：[1]中国空气动力研究与发展中心

出　　处：《空气动力学学报》1995年第1期72-76,共5页Acta Aerodynamica Sinica

摘　　要：本文给出了用ＮＳ方程对翼型非定常粘性大攻角绕流的数值模拟。控制方程为二级时均可压缩完全ＮＳ方程；湍流模型采用双层代数涡粘性模型￣［１］。使用近似因式分解ＡＤＩ差分格式离散求解，网格是用保角变换方法生成的相对翼型固定的Ｃ型网格。本文给出两类典型非定常绕流数值模拟结果：翼型过失速常攻角周期流动和大攻角强迫俯仰谐振非定常绕流。并与国外的实验和计算结果进行了比较，表明了本方法准确、高效的特点。The numerical simulations for unsteady viscous flows around airfoil using Navier-Stokes equations were developed,The two-dimensional time-averaged unsteady compressible full Navier-Stokes equations in strong conservation form.A two-layer algebraic eddy viscosity model and its modification were used in the solver. An approximate factoriza-tioh alternating-direction-implicit(ADI) time-marching algorithm and C-type body-fitted meshes systems generated by conforinal-transform meth-od, were used to study two primary type of unsteady flows: unsteady peri-odic flow over an airfoil at a fixed angle-of-attack past stall and un-steady flow over an airfoil in forced pitching oscillating.The resultscalculated are essential agreement with experiment data, proved effec-tiveness and accuracy of present method.

关 键 词：非定常流动 翼型 数值模拟 机翼 大功角绕流 

分 类 号：V211.41[航空宇航科学与技术—航空宇航推进理论与工程]