Drag coefficient \(C_D\) comparison between CFD codes and experimental data. ![]() Source: CODE \(C_l \ (AoA=0^o)\) \(C_l \ (AoA=5^o)\) \(C_l \ (AoA=10^o)\) \(C_l \ (AoA=15^o)\) Source UIUC Airfoil Coordinates Database (ag47c03-il) AG47c -03f: Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file: Drela AG47c -03f airfoil Max thickness 5.1 at 22.4 chord Max camber 1.3 at 33.4 chord Source UIUC Airfoil Coordinates Database (ag47ct02r-il) AG47ct -02f rot. Lift coefficient \(C_l\) comparison between CFD codes and experimental data. Max camber 3. In the table we put information from the experimental data for the selected AoA but also results from other CFD codes validated by NASA. Details: Dat file: Parser (n10-il) N-10 N-10 airfoil Max thickness 11.2 at 30 chord. 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 \(C_D\). Diese Profile sind in der UIUC Airfoil Data Site nicht enthalten and are into the 'Free Pack Airfoils' + For other airfoils files, consult the 'Free Pack Airfoils'. However, since we are working with small Mach number \(Ma=0.15\), the influence of compressibility is small. Profildatenbank Die untenstehenden Profile sind. 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. P is the position of the maximum camber divided by 10. ![]() ![]() In the example M2 so the camber is 0.02 or 2 of the chord. NACA 2412, which designate the camber, position of the maximum camber and thickness. The simulation of the 2D flow around NACA 0012 airfoil was carried out at \(Re=6000000\) (based on chord \(c = 1 \, m\)). This NACA airfoil series is controlled by 4 digits e.g.
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