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.
出处
《空气动力学学报》
CSCD
北大核心
1995年第1期72-76,共5页
Acta Aerodynamica Sinica
关键词
非定常流动
翼型
数值模拟
机翼
大功角绕流
usteady flow, airfoil,aerodynamic stalling , numericalsimulation.