Wing Simulation Using Naca 2412 and 2415 Airfoils with Variations in Angle of Attack for Lift and Drag

The geometry of an airfoil plays a critical role in shaping an aircraft's performance, especially during maneuvering. This study emphasizes the necessity of conducting a comprehensive geometric analysis to better understand the effects of airfoil design. In pursuit of optimizing airfoil performance, we conducted extensive tests on NACA 2412 and 2415 series airfoil geometries using the ANSYS Fluent software. The tests employed Aluminum Alloy 1067 material and a wind speed of 300 m/s, encompassing a range of angle of attack variations from 0 to 180 degrees. The simulation results provided valuable insights into the velocity and pressure distributions surrounding the airfoil. Of particular interest, at an angle of 15 degrees, the NACA 2412 airfoil exhibited a maximum drag force of 69.670 N and a maximum lift force of 550.300 N. The corresponding drag and lift coefficients were 0,1516378 N and 1,1977364 N. For the NACA 2415 airfoil, the maximum drag and lift forces were 71.470 N and 564.500 N, respectively, with corresponding drag and lift coefficients of 0,1541963 N and 1,2179072 N.


INTRODUCTION
The geometry of an airfoil on an aircraft's wing plays a pivotal role in shaping its aerodynamic performance during various flight maneuvers [1] [2].Among the myriad airfoil shapes, one prominent design is the NACA airfoil, developed by the National Advisory Committee for Aeronautics (NACA) [3][4] [5].
The NACA airfoil represents a geometric configuration that, when subjected to airflow, generates both lift and drag forces [6][7].This phenomenon is fundamental in aviation, where the lift force surpasses the drag force, enabling flight [8] [9].
The interaction of a fluid with an airfoil influences multiple variables, including speed, mass density, pressure, and temperature [10] [11].This dynamic interplay forms the bedrock of aerodynamics, influencing the advancement of aviation technology and numerous other engineering domains [12].
The lift force generated during flight results from the aerodynamic pressure differential created as the fluid flows over and under the wings of an aircraft operating at high altitudes [13][14] [15].

Aerodynamic research in airfoil modeling
has seen extensive exploration through analytical methods, aerodynamic formulas, wind tunnel experiments, and more recently, the adoption of Computational Fluid Dynamics (CFD) using tools like ANSYS, but first designed in SolidWorks software [16].
SolidWorks is a software called solid "parametric modeling" which is intended for drawing designs with 3-Dimensional design modeling [17] [18].SolidWorks itself is a 3D As a reference, this research was conducted to contribute references regarding the aerodynamics of aircraft wings that use the NACA 2412 and 2415 airfoil geometry in the future.Apart from that, this research model can also be used as a reference in designing wind turbine blades [22] [23].
In this study, we focus on two specific 4digit series NACA airfoil models: NACA 2412 and NACA 2515 [24] [25].Our research endeavors to unveil the impact of the angle of attack on various aerodynamic parameters, including the distribution of speed, pressure, lift coefficient, and thrust coefficient.The angles of attack examined encompass 0, 3, 6, 9, 12, 15, and 18 degrees.Furthermore, this study aims to shed light on the variations in lift and drag distribution across the airfoil.
The research method carried out in this research is a computational analysis technique or Computational Fluid Dynamic (CFD) using ANSYS R.18 software [16].The analysis stage is shown in Figure 1.Before running the simulation, the design drawing from SolidWorks is imported into ANSYS Modeler and then the domain settings are carried out.The next step is Mesh, mesh is the process of dividing the components to be analyzed into small or discrete elements where the better the quality of the mesh, the higher the level of convergence [30][31], so we will get higher quality data.The final step before running the simulation is setting fixed parameters such as aircraft speed, model, parameters to be exported, and others.From the simulation results that have been carried out, there is a result feature that can be exported in the form of a data sheet or test results data, if you carry out all the steps correctly.The test result data is shown in table 2. Table 2 shows the magnitude of the drag where A is the area of the model, V is the fluid velocity, Fl is lift force, Fd is drag force, Cl is lifted force coefficient, Cd is drag force coefficient [17] [18].The lift and thrust coefficients can be seen in Tables 3 and 4  Based on the results of the calculations above, variations in the angle of attack on the drag and lift forces can be compared as shown in Figure 16 and Figure 17.This large lifting force coefficient is needed so that the force can overcome the weight force due to the earth's gravitational pull or the lifting force must be able to oppose the earth's gravitational pull so that the object can be lifted and maintain its position in the sky.

Figure 3 .
Figure 3. NACA airfoil wing design using solid works software Based on the results of simulations carried out on variations in the angle of attack of the NACA 2412 and 2415 airfoils, the velocity and pressure contours around the airfoil geometry were obtained.The pressure and velocity contours on NACA 2412 are shown in Figure 4 to Figure 9.The pressure and velocity contours on NACA 2415 are shown in Figure 10 to Figure 15.Meanwhile, the results of the lift force and drag force from the simulation results are shown in Table2.

Figure 4 .Figure 5 .
Figure 4. NACA 2412 simulated velocity contours at an angle of attack of 0 degree

Figure 6 .Figure 7 .Figure 8 .Figure 9 .Figure 10 .Figure 11 .Figure 12 .Figure 13 .Figure 14 .Figure 15 .Figure 4 to
Figure 6.NACA 2412 simulated velocity contours at an angle of attack of 18 degree force and lift force on NACA 2412 and 2415 with varying angles of attack so that the calculation of the lift force coefficient can be calculated using the formula   =   0.5 × 2 × and the drag force coefficient is calculated using the formula   =   0.5 × 2 ×

Figure 16 .
Figure 16.Graph of variation of angle of attack with drag coefficient Figures 16 and Figure17 show the coefficients of drag and lift based on variations in the angle of attack.From the picture, it can be seen that the largest dragging force and lifting force are at an angle of attack of 15 0 .

Figure 17 .
Figure 17.Graph of variation of angle of attack with lift coefficient

Table 1 .
Initial research data shown in Table1.

Table 2 .
Simulation results of NACA 2412 and 2515 with varying angles of attack

Table 4 .
Lift and drag coefficients of NACA 2415