STUDI NUMERIK PERBANDINGAN KARAKTERISTIK
AIRFOIL NACA 4412 DAN NACA 4415
MEMPERTIMBANGKAN GROUND EFFECT TERHADAP
VARIASI SUDUT SERANG
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Institusion
INSTITUT TEKNOLOGI DIRGANTARA ADISUTJIPTO
Author
Dinda Farrasizdhihar, Sahnaz
Subject
T Technology (General)
Datestamp
2024-04-05 03:25:45
Abstract :
Wing-in-ground (WIG) craft is a type of aircraft that has a low-flying mechanism by utilizing the ground effect to improve its aerodynamic performance. The phenomenon of the ground effect on aerodynamic characteristics is a function of altitude. A numerical study on the NACA 4412 and 4415 airfoils was carried out using the Reynolds-Averaged Navier-Stokes (RANS) incompressible approach at a velocity of 28 m/s. In this study, the study was conducted using a 2D domain and the Spalart-Allmaras (S-A) turbulence model. From the simulation results obtained aerodynamic characteristics of NACA 4412 with the highest Cl value at the angle of attack 9º and the lowest Cd at the angle of attack of 3º. As for the aerodynamic performance represented by Cl/Cd, the highest value was obtained at the height and angle of attack. The airfoil comparison results showed the best CFD results on two 2D airfoil models occurred at the altitude of 0.1c and angles of attack 3° and 6° with Cl/Cd=115.1604. The lift coefficient value for NACA 4415 was higher than NACA 4412. The drag coefficient for NACA 4415 tended to increase, while for NACA 4412 the drag coefficient decreased due to the differences in camber thickness and meshing density. The characteristics of the two airfoils were not so different where the lift coefficient was at its maximum value at angles of attack of 9°, 12°, and 15°, while the drag coefficient would increase with increase of angle of attack so that it could stall or decrease the performance.
Wing-in-ground (WIG) craft is a type of aircraft that has a low-flying mechanism by utilizing the ground effect to improve its aerodynamic performance. The phenomenon of the ground effect on aerodynamic characteristics is a function of altitude. A numerical study on the NACA 4412 and 4415 airfoils was carried out using the Reynolds-Averaged Navier-Stokes (RANS) incompressible approach at a velocity of 28 m/s. In this study, the study was conducted using a 2D domain and the Spalart-Allmaras (S-A) turbulence model. From the simulation results obtained aerodynamic characteristics of NACA 4412 with the highest Cl value at the angle of attack 9º and the lowest Cd at the angle of attack of 3º. As for the aerodynamic performance represented by Cl/Cd, the highest value was obtained at the height and angle of attack. The airfoil comparison results showed the best CFD results on two 2D airfoil models occurred at the altitude of 0.1c and angles of attack 3° and 6° with Cl/Cd=115.1604. The lift coefficient value for NACA 4415 was higher than NACA 4412. The drag coefficient for NACA 4415 tended to increase, while for NACA 4412 the drag coefficient decreased due to the differences in camber thickness and meshing density. The characteristics of the two airfoils were not so different where the lift coefficient was at its maximum value at angles of attack of 9°, 12°, and 15°, while the drag coefficient would increase with increase of angle of attack so that it could stall or decrease the performance.
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