PENGARUH LEADING EDGE SERRATION DAN TRAILING
EDGE SERRATION TERHADAP KARAKTERISTIK
AERODINAMIKA PADA SAYAP DENGAN AIRFOIL NACA 4412
MELALUI SIMULASI KOMPUTASIONAL
Total View This Week0
Total View This Week0
Institusion
INSTITUT TEKNOLOGI DIRGANTARA ADISUTJIPTO
Author
Anlanosa Dioga, Aulia
Subject
T Technology (General)
Datestamp
2024-05-06 02:44:14
Abstract :
An airplane wing is the main component of an airplane, and has the function of producing lift or lifting force on the airplane. On the aircraft wing there is a primary flight control surface, and a secondary flight control surface which functions as the aircraft's steering area. The leading edge is located at the front of the wing (upper surface), while the trailing edge is located at the back of the wing (lower surface). In writing and researching this thesis report, we carried out numerical simulations. This research uses angles of attack -10°, 0°, 10°, 15°, 20°, 30°. The simulation was carried out during cruising flight at a speed of 30 m/s above sea level. Aerodynamic simulation on the NACA 4412 airfoil model without and using serration on the leading edge and trailing edge and knowing the effect of serration on the NACA 4412 airfoil model on the leading edge and trailing edge on aerodynamic characteristics using ANSYS CFX software. Meanwhile, in carrying out calculations or data processing for the lift coefficient (Cl) and drag coefficient (Cd) values for each modified NACA 4412 airfoil model, where the ? value is equal to 1.225 N, and the S value is 8.404 m² for non serrated while leading edge and trailing edge serrated 7,478 m². It was found that serrated on the leading edge can increase quite a lot of lift and drag, in contrast to the serrated trailing edge which can increase lift but not significantly increase drag.
An airplane wing is the main component of an airplane, and has the function of producing lift or lifting force on the airplane. On the aircraft wing there is a primary flight control surface, and a secondary flight control surface which functions as the aircraft's steering area. The leading edge is located at the front of the wing (upper surface), while the trailing edge is located at the back of the wing (lower surface). In writing and researching this thesis report, we carried out numerical simulations. This research uses angles of attack -10°, 0°, 10°, 15°, 20°, 30°. The simulation was carried out during cruising flight at a speed of 30 m/s above sea level. Aerodynamic simulation on the NACA 4412 airfoil model without and using serration on the leading edge and trailing edge and knowing the effect of serration on the NACA 4412 airfoil model on the leading edge and trailing edge on aerodynamic characteristics using ANSYS CFX software. Meanwhile, in carrying out calculations or data processing for the lift coefficient (Cl) and drag coefficient (Cd) values for each modified NACA 4412 airfoil model, where the ? value is equal to 1.225 N, and the S value is 8.404 m² for non serrated while leading edge and trailing edge serrated 7,478 m². It was found that serrated on the leading edge can increase quite a lot of lift and drag, in contrast to the serrated trailing edge which can increase lift but not significantly increase drag.
Download
book
BibTex
Latex, Jabref
cloud_download
Original Resource
url resource Institution
