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A CFD assessment to subsonic flow around NACA4412 | ||
| Journal of Engineering and Sustainable Development | ||
| Article 1, Volume 15, Issue 4, 2011, Pages 173-188 | ||
| Author | ||
| Ali Abud AL-Nabi Abass | ||
| Abstract | ||
| The purpose of this study is determined values of Mach Number (Ma) for Subsonic flow around NACA4412 which is begun shock wave and known the location it. A 2-dimensional triangular C-type grid is used to match the reference measurements at an airfoil cross-section was taken from NACA 4412 from leading edge to trailing edge. The Mach numbers which used are (0.1 to 0.9) respectively and angles of attack (2.31° and 0.0°)for three cases inviscid and viscous flow with choose two cases (K epsilon RNG and Spalart-Allmaras turbulent models). The numerical results show that the inviscid and two turbulence models well predict the shock wave location and size as well as flow properties along the airfoil surface. The Lift Force Coefficient (CL) decrease and the Drag Force Coefficient (CD) increase with using viscous term as well as pressure coefficient (CP) give fit location for the shock wave | ||
| Keywords | ||
| Computational fluid dynamics; Turbulence models; subsonic flow; Spalart; Allmaras Model; epsilon rng model; grid technique | ||
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