Airfoil Comparison
Select airfoils from the airfoil database or add your own airfoils and compare the airfoil shape and lift/drag polars.
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(naca4424-il) NACA 4424 | NACA 4424 airfoil Max thickness 24% at 29.4% chord Max camber 4% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (naca4424-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca4424-il | 50,000 | 9 | 2 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca4424-il | 50,000 | 5 | 8.8 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca4424-il | 100,000 | 9 | 30.8 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca4424-il | 100,000 | 5 | 33.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca4424-il | 200,000 | 9 | 53.6 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca4424-il | 200,000 | 5 | 45.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca4424-il | 500,000 | 9 | 64.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca4424-il | 500,000 | 5 | 55.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca4424-il | 1,000,000 | 9 | 73.6 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca4424-il | 1,000,000 | 5 | 64.5 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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