Drag coefficient \(C_D\) comparison between CFD codes and experimental data. Lift coefficient \(C_l\) comparison between CFD codes and experimental data. There are links to the original airfoil source and dat file and the details page with polar diagrams for a range of Reynolds numbers. Click on an airfoil image to display a larger preview picture. In the table we put information from the experimental data for the selected AoA but also results from other CFD codes validated by NASA. Airfoil database search (NACA 4 digit Symmetrical) Search the 1638 airfoils available in the databases filtering by name, thickness and camber. During the late 1920s and into the 1930s, the NACA developed a series of thoroughly tested airfoils and devised a numerical designation for each airfoil a four digit number that represented the airfoil section’s critical geometric properties. The results obtained using SimFlow are presented in the form of Table 2 and Table 3, and plots showing lift coefficients \(C_l\) and drag coefficients \(C_D\). However, since we are working with small Mach number \(Ma=0.15\), the influence of compressibility is small. The speed of sound was evaluated at \(347 \, \frac\omega \ SST\) model with Low Re wall function applied at airfoil.Īt this point we would like to mention that CFD codes validated by NASA were density-based. The simulation of the 2D flow around NACA 0012 airfoil was carried out at \(Re=6000000\) (based on chord \(c = 1 \, m\)).
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