Studi CFD Aliran Udara Di Sekeliling WING NACA0015 Yang Dilengkapi Split Flap

摘要

The values of lift and drag coefficients of airfoil which is formed by Wing NACA0015 can be obtained through numerical approach, for example by using CFX. The objectives of this study are to simulate and to get the optimum angle of deflection flap and angle of attack and to describe the lift coefficient (CL) and the drag coefficient (CL) in various speed and temperature.udThis study is to explain the work of wing NACA0015 that operates when take off and landing process only. At the time the speed is relative low. The fist step is to build a model of Wing NACA0015 using solidwork. After that the meshing process was carried out using Ansys CFD software. Those processes resulted parameter, that are : lift coefficient, drag coefficient, distribution of speed and the pressure that accur.udThe result of this study shows that in the take off and landing process the optimum deflection flap is on 20o and the optimum angle of attack is on 8o. The study also found the highest lift coefficient that is 0,604 at 30 m/s speed and 0,577 at 15o C temperature, meanwhile for the highest drag coefficient that is 0,039 at 5 m/s speed and 0,0335 at 40o C temperature. The lowest lift coefficient that is 0,547 at 5 m/s speed and 0,569 at 40o C temperature, meanwhile for the lowest drag coefficient thats is 0,032 at 30 m/s speed and 0,331 at 15o C temperature.