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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(naca2424-il) NACA 2424 | NACA 2424 airfoil Max thickness 24% at 29.7% chord Max camber 2% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (naca2424-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca2424-il | 50,000 | 9 | 1.8 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2424-il | 50,000 | 5 | 15.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2424-il | 100,000 | 9 | 36.8 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2424-il | 100,000 | 5 | 33.2 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2424-il | 200,000 | 9 | 49 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2424-il | 200,000 | 5 | 40.3 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2424-il | 500,000 | 9 | 55 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2424-il | 500,000 | 5 | 49.9 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2424-il | 1,000,000 | 9 | 65.9 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2424-il | 1,000,000 | 5 | 58.3 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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