ANALISIS NUMERIK KARAKTERISTIK AERODINAMIKA
PADA AIRFOIL NACA 2412 DENGAN TAMBAHAN
KONFIGURASI FLAP DAN SLAT
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Institusion
INSTITUT TEKNOLOGI DIRGANTARA ADISUTJIPTO
Author
Syahrizal, Syahrizal
Subject
T Technology (General)
Datestamp
2024-04-05 03:26:44
Abstract :
Technological advances in the modern era are getting faster. One of which is an airplane which makes the distance and travel time more efficient and economical. The initial idea that formed the basis of the Easy-Fly project is to design an ultra-light STOL (Short Take-off and Landing) aircraft with extremely low drag and speed characteristics. The design and analysis applied to the STOL aircraft is a high-lift system, namely the flaps and slats are designed to be retractable to have low drag characteristics in cruise conditions and a very high maximum lift coefficient in takeoff and landing conditions characterized by a speed of 20 m/s. A numerical analysis was performed computationally using CFD (Computational Fluid Dynamics) with variations of single-slotted flap and slat configuration on the NACA 2412 airfoil at various angles of attack. Based on the results of the study, the flap deflection configuration 30° resulted in a CLmax of 2.7127 and a flap deflection 40° CLmax of 2.77057 at an angle of attack 14°. The application of the slat configuration on the NACA 2412 airfoil was able to delay air separation until it reached a maximum angle of attack 24° at flap deflection 30° and the CLmax value increased to 3.55792 at flap deflection 30° and 3.41132 at flap deflection 40°. In addition to the high-lift system configuration on the NACA 2412 airfoil, the camber and effective chord line of the airfoil changed, causing a significant increase in the values of CL, Cd and stall angle.
Technological advances in the modern era are getting faster. One of which is an airplane which makes the distance and travel time more efficient and economical. The initial idea that formed the basis of the Easy-Fly project is to design an ultra-light STOL (Short Take-off and Landing) aircraft with extremely low drag and speed characteristics. The design and analysis applied to the STOL aircraft is a high-lift system, namely the flaps and slats are designed to be retractable to have low drag characteristics in cruise conditions and a very high maximum lift coefficient in takeoff and landing conditions characterized by a speed of 20 m/s. A numerical analysis was performed computationally using CFD (Computational Fluid Dynamics) with variations of single-slotted flap and slat configuration on the NACA 2412 airfoil at various angles of attack. Based on the results of the study, the flap deflection configuration 30° resulted in a CLmax of 2.7127 and a flap deflection 40° CLmax of 2.77057 at an angle of attack 14°. The application of the slat configuration on the NACA 2412 airfoil was able to delay air separation until it reached a maximum angle of attack 24° at flap deflection 30° and the CLmax value increased to 3.55792 at flap deflection 30° and 3.41132 at flap deflection 40°. In addition to the high-lift system configuration on the NACA 2412 airfoil, the camber and effective chord line of the airfoil changed, causing a significant increase in the values of CL, Cd and stall angle.
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