CAJ | 학술논문

使用模态法构造结构模型,研究了在时域内耦合结构模型和气动模型预测三维翼颤振的方法;求解N-S方程计算非定常气动力.Newmark算法简化颤振方程.采用无限平面插值方法耦合结构网格和气动网格;使用弹性系数算法和局部网格重构法重构非结构气动网格,以确保结构方程和气动方程进行耦合求解.AGARD 445.6翼算例检验了计算方法的可行性.
사용모태법구조결구모형,연구료재시역내우합결구모형화기동모형예측삼유익전진적방법;구해N-S방정계산비정상기동력.Newmark산법간화전진방정.채용무한평면삽치방법우합결구망격화기동망격;사용탄성계수산법화국부망격중구법중구비결구기동망격,이학보결구방정화기동방정진행우합구해.AGARD 445.6익산례검험료계산방법적가행성.
A numerical method coupling Navier-Stokes equations and structural modal equations for predicating Three-Dimensional transonic wing flutter was described and modal approach was used for predicting the structural response. The Newmark algorithm was used to solve flutter equation. Infinite-plate spline method transformed datum between structural grid and aerodynamic grid. Aerodynamic grid was deformed and regenerated based on spring-based smoothing method and local remeshing method. The flow and structural solvers were fully coupled within each physical time step. The computed flutter boundary of AGARD wing 445.6 for free stream Mach numbers ranging from 0.499 to 1.141 agreed well with the experiment.