Studi Eksperimental dan Simulasi Numerik Karakteristik Aerodinamika Airfoil NACA 4412

Abstract

The objective of this study is to investigate the aerodynamics characteristic of airfoil NACA 4412 based on experiment and numerical simulation. A 3D airfoil with chord length (C) of 100 mm and span-width (S) of 200 mm was fabricated in order to be tested by subsonic wind tunnel at inlet air velocity of 10 m/s, whereas numerical study was realised by 2D airfoil reffering to geometrics in the experiment. The structured mesh with 810,000 elements number was constructed by Gambit meshing tools up to reach the near wall resolution of Δy+ = 17.2. Spallart-Almaras turbulence model was applied in the simulation of RANS study.The effect of various angle of attack (α) between -5 and 20 was investigated for both methods in terms of the aerodinamic characteristics such as lift coefficient (CL), drag coefficient (CD), and lift-drag ratio (L/D). The pressure coefficient (CP) and flow visualisations around the airfoil were generated by simulation method. In general, the results show that the data resulted by both methods agree well compared to the other studies, mainly for the lift and drag coefficients. Both coefficients increase with rising the angle of attack before approaching a stall condition at α = 15 o . From this point, lift coefficient drops significantly due to large turbulent wake that reduces to lift and influence to drag. The change of attack angles influences the shifting of both stagnation and expansion points in the leading edge, furthermore it causes the overall aerodynamic characteristics. The increase of pressure difference between upper and lower surfaces of airfoil body causes the rise of lift.

Ship Performances CFD Analysis of Hydrofoil-Supported High-Speed Catamaran Hull Form

“…The aspect ratio (AR) of the foil is 7, where AR is defined as the ratio of the span (𝑠) to the chord (𝑐). Prior research on the NACA 4412 indicated that the angle of attack at which the highest lift-to-drag ratio is achieved is between 4° and 6° [34,35]. Hence, the foils were adjusted at an angle of attack of 5.25°, measured in a counterclockwise direction from the vessel's course direction, corresponding to the positive xaxis.…”

Penggunaan Komputasi pada Analisis Dinamika Fluida di Airfoil NACA M-15

“…Sedangkan memperbesar sudut α, berpengaruh terhadap terjadinya peningkatan nilai Cp pada lower surface airfoil dan penurunan nilai Cp pada upper surface airfoil. Adapun pada kajiannya, Effendy fokus pada investigasi karakteristik aerodinamika airfoil NACA 4412 dengan melakukan ekserimen pada subsonic wind tunnel dan simulasi numerik [4]. Simulasi dikerjakan dengan memodelkan airfoil 2D, mesh terstruktur dan model turbulensi Spalart Allmaras (SA) dengan memvariasikan sudut serang antara -5° hingga 20° dengan kecepatan aliran 10 m/s.…”

Studi Numerik dan Eksperimen Aerodinamika Airfoil NACA 24112

“…Perubahan sudut serang airfoil memainkan peran sangat penting terhadap karakteristik aerodinamika aliran, seperti koefisien lift, koefisien drag, rasio lift-drag(L/D), koefisien tekanan dan profil aliran [2]. Pada kecepatan yang tetap gaya angkat akan meningkat seiring dengan peningkatan sudut serang hingga mencapai nilai maksimumnya dan kemudian tiba tiba turun, fenomena ini disebut stalling [1].…”