ANALISIS KEBISINGAN TRAILING EDGE FINLET PADA AIRFOIL NACA 0012 MENGGUNAKAN METODE LARGE EDDY SIMULATION
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Institusion
INSTITUT TEKNOLOGI DIRGANTARA ADISUTJIPTO
Author
Luthvia Amarozia, Adinda
Subject
T Technology (General)
Datestamp
2024-02-15 08:25:15
Abstract :
Noise mitigation is essential for aviation industry due to increasingly stringent noise regulations. One of the noise sources on an airplane is located on the trailing edge. The noise can be reduced by surface treatment which is adding finlet on the trailing edge. One method of noise analysis can be done computationally with CFD Computational Fluid Dynamic and FWH Ffwocs William and Hawkings acoustics. The numerical approach used is LES Large Eddy Simulation for turbulent analysis. The computational process generated OASPL Overall Sound Pressure Level values with angle of attack AoA variations on NACA 0012 in the 0° to 17° angle range, receiver position 3, with an airspeed of 71.3 m/s, and using clear airfoil, and finlet airfoil configurations. Based on the research results, the highest OASPL value is located at AoA 16° receiver 1 with clear airfoil of 105.983 dB and trailing edge finlet of 99.4646 dB. The application of finlet on the trailing edge can reduce noise by 6.6879 dB. The application of finlet on the trailing edge can reduce noise by 6.6879 dB. The application of finlets on the trailing edge has not met the ICAO noise standard rule of noise reduction of 7 dB because the simulation performed was a 2D analysis where there are limitations in adding the number of finlets and the space between finlets on the trailing edge which can only be applied to 3D analysis. The advantages obtained in this 2D analysis were that it could reduce the cost and time used during computation and overall the finlet configuration on the trailing edge could provide a solution in noise reduction on the NACA 0012 airfoil.
Noise mitigation is essential for aviation industry due to increasingly stringent noise regulations. One of the noise sources on an airplane is located on the trailing edge. The noise can be reduced by surface treatment which is adding finlet on the trailing edge. One method of noise analysis can be done computationally with CFD Computational Fluid Dynamic and FWH Ffwocs William and Hawkings acoustics. The numerical approach used is LES Large Eddy Simulation for turbulent analysis. The computational process generated OASPL Overall Sound Pressure Level values with angle of attack AoA variations on NACA 0012 in the 0° to 17° angle range, receiver position 3, with an airspeed of 71.3 m/s, and using clear airfoil, and finlet airfoil configurations. Based on the research results, the highest OASPL value is located at AoA 16° receiver 1 with clear airfoil of 105.983 dB and trailing edge finlet of 99.4646 dB. The application of finlet on the trailing edge can reduce noise by 6.6879 dB. The application of finlet on the trailing edge can reduce noise by 6.6879 dB. The application of finlets on the trailing edge has not met the ICAO noise standard rule of noise reduction of 7 dB because the simulation performed was a 2D analysis where there are limitations in adding the number of finlets and the space between finlets on the trailing edge which can only be applied to 3D analysis. The advantages obtained in this 2D analysis were that it could reduce the cost and time used during computation and overall the finlet configuration on the trailing edge could provide a solution in noise reduction on the NACA 0012 airfoil.
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