![]() It is concluded that Spalart-Allmaras model and k-ω SST model are capable of providing the most accurate prediction for lift coefficient at a low angle of attack for both airfoils. Moreover, the aim of the present study is to demonstrate the difference in aerodynamic characteristics of the airfoils in order to find aerodynamically more advantageous airfoil. This paper presents an evaluation of five different turbulence models by comparing the numerical data derived from these models using ANSYS Fluent with experimental data at a Reynolds number and a Mach number of 0.05 × 10^6 and 0.015 respectively based on the centerline chord of the airfoil for the flow over NACA 0012 and NACA 2412 airfoils. Keywords: Lift coefficient on airfoil with internal passage, wind tunnel experiments, range of angle of attack, Subsonic wind tunnel, Selective Laser Sintering (SLS) ![]() The range of angle of attack (α) was between zero and 40°. This reduces the boundary layer separation at higher angle of attack from the airfoil. We can conclude that point of separation for 3D NACA 2412 airfoil with internal passage is shifted towards trailing edge. Experimental results indicate that the lift coefficient for 3D NACA 2412 airfoil with internal passage was marginally higher than the lift coefficient for 3D NACA 2412. The density of air was taken to be 1.2 kg/m 3. #NACA 2412 AIRFOIL FREE#The range of free stream velocity measured upstream with Pitot tube was in the range of 8 to 18ss m/s. The chord length (c) was 100 mm and the span (b) was 100 mm. Both the airfoils were of same dimensions and profile. ![]() The objective of this research was to compare the experimental coefficient of lift and drag for a NACA 2412 airfoil with that for NACA 2412 airfoil with internal passage. Wind tunnel experiments were carried out in a subsonic wind tunnel in Fluid Mechanics Laboratory at MITCOE, Pune. ![]()
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