CAJ | 학술논문

采用能够恢复可压缩Navier-Stokes方程的耦合双分布(DDF)格子Boltzmann方法(LBM)模拟了贴体网格下的NACA0012翼型绕流.首先在Ma＝0.5,α＝0.0,Re＝5 000状态下通过模拟低雷诺数流动检验了该方法;然后分别在Ma＝0.5,0.85和1.2,α＝-0.05,1.0和0.0状态下进行了模拟,并在Ma＝0.85时通过加密网格得到了更好的结果.为了避免转捩问题采用了无粘边界条件进行模拟,但得到的压力系数与实验结果吻合良好,证明了该方法的可靠性并显示了其模拟可压缩的潜力.该方法在翼型绕流上的应用为湍流流动的数值模拟提供了基础.
채용능구회복가압축Navier-Stokes방정적우합쌍분포(DDF)격자Boltzmann방법(LBM)모의료첩체망격하적NACA0012익형요류.수선재Ma＝0.5,α＝0.0,Re＝5 000상태하통과모의저뢰낙수류동검험료해방법;연후분별재Ma＝0.5,0.85화1.2,α＝-0.05,1.0화0.0상태하진행료모의,병재Ma＝0.85시통과가밀망격득도료경호적결과.위료피면전렬문제채용료무점변계조건진행모의,단득도적압력계수여실험결과문합량호,증명료해방법적가고성병현시료기모의가압축적잠력.해방법재익형요류상적응용위단류류동적수치모의제공료기출.
The flow around airfoil NACA0012 enwrapped by the body-fitted grid is simulated by a coupled double-distribution-function (DDF) lattice Boltzmann method (LBM) for the compressible Navier-Stokes equations. Firstly, the method is tested by simulating the low Reynolds number flow at Ma=0.5,α=0.0, Re=5 000. Then the simulation of flow around the airfoil is carried out at Ma=0.5, 0.85, 1.2; α=-0.05, 1.0, 0.0, respectively. And a better result is obtained by using a local refined grid. It reduces the error produced by the grid at Ma=0.85. Though the inviscid boundary condition is used to avoid the problem of flow transition to turbulence at high Reynolds numbers, the pressure distribution obtained by the simulation agrees well with that of the experimental results. Thus, it proves the reliability of the method and shows its potential for the compressible flow simulation. The successful application to the flow around airfoil lays a foundation of the numerical simulation of turbulence.