격자 정밀도에 따른 2차원NACA4412 공력특성 분석

초록

The numerical investigation of aerodynamic performance at a Reynolds number of 2 × 106 was conducted toexamine the difference according to the number of nodes in the computational grids. Three computationalgrids with different numbers of nodes were used in this study. The two-dimensional NACA 4412 airfoil wasanalyzed, and investigation was performed with angles of attack ranging from 0° to 20° for all three cases. The pressure distribution, velocity, pressure coefficient, lift coefficient, drag coefficient, and lift-to-drag ratiowere analyzed to investigate the aerodynamic performance according to the computational grid nodes andangles of attack. The results confirmed that the aerodynamic performances of three cases were closelycomparable under low angle of attack. On the other hand, the difference in aerodynamic performance betweencases with different numbers of nodes increased as the angle of attack increased. Overall, the angle of attackat which the lift coefficient and lift to drag ratio reach maximum values changed as the increase of numberof nodes in computational grids. The results showed that the numerical predictions of aerodynamicperformance, such as lift coefficient and lift to drag ratio, were affected by the number of grid nodes,particularly under high angle of attack conditions.

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