Drag coefficient \(C_D\) comparison between CFD codes and experimental data. These graphs show test results for several different Reynolds. Note that for the symmetrical shape the lift coefficient is zero at zero angle of attack. Lift coefficient \(C_l\) comparison between CFD codes and experimental data. Figure A-1 shows data for the NACA 0012 airfoil, a classic symmetrical shape that is used for everything from airplane stabilizers and canards to helicopter rotors to submarine sails. In the table we put information from the experimental data for the selected AoA but also results from other CFD codes validated by NASA. 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 \(C_D\). Max camber 2 at 39. However, since we are working with small Mach number \(Ma=0.15\), the influence of compressibility is small. Details: Dat file: Parser (n2414-il) NACA 2414 NACA 2414 airfoil Max thickness 14 at 29.5 chord. 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. Airfoil database search My airfoils Airfoil plotter Airfoil comparison Reynolds number calc NACA 4 digit generator NACA 5 digit generator Information. 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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