부산대학교 도서관

In this study, aerodynamic analyses for several previous wind-tunnel test models such as F-5, ONERA M6, RAE wing body, EGLIN wing with pylon and finned store, generic fighter, F-16 SDM, and business jet etc. have been performed using lattice Boltzman method (LBM) and compared with experimental data. The purpose of this study is to investigate the numerical accuracy, current limitation, and computational efficiency of a meshless particle-based methodology using XFlow software of which efficient octree mesh generator can solve complex geometries easily. It is also shown in this paper that there is a critical particle resolution level to guarantee relatively accurate analysis results using LBM. In order to achieve the purpose of the present study, inviscid and viscous flow analyses for several experimental models have been widely analyzed for different element resolution ratio (ERR) and validated with wind-tunnel test data in subsonic, transonic, and supersonic flow regimes. It is importantly found that the most important parameter in using LBM is the ERR, and the results for less than 5% thickness ratio wing show mostly good agreement with test data, but shows somewhat discrepancies with test data for wings with more than 10% thickness ratio and highly-swept wing even in using high ERR. Finally, sloshing phenomena of three different water tank models have been analyzed considering free-surface wave motions and compared with experimental data herein. It is found from the present results that predicted impact peak pressures during sloshing motion using LBM approach are much more good agreement than those predicted by conventional CFD approach.