Abstract
In this research, COMSOL Multiphysics Simulation program was used to calculate the coefficients of drag and lift (Cd & CL) and the glide ratio (GR) or so-called CL/Cd ratio for five airfoils (namely: NACA 2412, NACA 2415, NACA 2418, NACA 4412, and NACA 4415) with two criteria (Reynolds's No. 1 × 105 and 2 × 105). We obtained multiple data from the parameters above by changing the angle of attack (α) each time from 0° to 10°. After that, a comparison was made among all date to obtain the highest glide ratio of all airfoils. Moreover, we obtained the highest stability in angle adjustment during operation. The results drawn as diagrams to understand the relationships. The results give us a hint of which airfoil is preferable to use due to wind velocity whether it is high or low and thus can be related to weather conditions in Iraq. Moreover, we can decide which airfoil is the optimum due to the angle of attack adjustment when the angle reaches its optimum value of glide ratio.
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