摘要
应用代数法和椭圆型方程优化相结合的方法生成翼身组合体块结构网格。采用有限体积空间离散法和五步Runge-Kutta显式时间推进法求解N-S方程。基于雷诺平均N-S(RANS)方程,选用Spalart-Allma-ras(SA)一方程模型模拟紊流。根据N-S方程定常计算结果,采用升力曲线、俯仰力矩曲线、后缘压力发散、跨声速激波位置以及机翼表面极限流线等几种判据,对跨声速机翼的抖振初始迎角进行了合理的预测分析。
Algebraic method combined with optimal elliptic partial differential equations is used to generate multiblock grids for a wing/body junction.Finite-volume scheme and five-stage Runge-Kutta explicit scheme are applied to solve the three-dimensional N-S equations.Based on Reynolds-Averaged N-S（RANS）equations,Spalart-Allmaras（SA） One-Equation turbulence model is employed to simulate the turbulent flows.A steady N-S solver is applied to the wing/body junction in transonic flight,then the buffet onset angle of shock induced buffet is reasonably estimated with various steady aerodynamic parameters of lift curve,pitching moment curve,tailing edge pressure deviation,reversal in shock movement and wing surface streamlines.
出处
《航空学报》
EI
CAS
CSCD
北大核心
2008年第4期840-844,共5页
Acta Aeronautica et Astronautica Sinica
关键词
块结构网格
有限体积法
N-S方程
紊流模型
抖振
multiblock grids
finite-volume method
N-S equations
turbulence model
buffet
