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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(naca0015-il) NACA 0015 | NACA 0015 airfoil Max thickness 15% at 30% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(m21-il) NACA M21 AIRFOIL | NACA/Munk M-21 airfoil Max thickness 12% at 30% chord Max camber 6% at 30% chord | Remove Airfoil details Airfoil plotter |
(fx38153-il) FX 38-153 AIRFOIL | Wortmann FX 38-153 airfoil Max thickness 15.5% at 43.5% chord Max camber 2.1% at 80.4% chord | Remove Airfoil details Airfoil plotter |
(ag10-il) AG10 | Drela AG10 airfoil Max thickness 4.7% at 16% chord Max camber 1.7% at 32.1% chord | Remove Airfoil details Airfoil plotter |
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Polars for (naca0015-il,m21-il,fx38153-il,ag10-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca0015-il | 50,000 | 9 | 24.7 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0015-il | 50,000 | 5 | 26.9 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0015-il | 100,000 | 9 | 37.5 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0015-il | 100,000 | 5 | 37.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0015-il | 200,000 | 9 | 49.6 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0015-il | 200,000 | 5 | 48.6 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0015-il | 500,000 | 9 | 66.4 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0015-il | 500,000 | 5 | 63.2 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0015-il | 1,000,000 | 9 | 77.9 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0015-il | 1,000,000 | 5 | 75.1 at α=10.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m21-il | 50,000 | 9 | 5.4 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m21-il | 50,000 | 5 | 22.2 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m21-il | 100,000 | 9 | 29.8 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m21-il | 100,000 | 5 | 48.5 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m21-il | 200,000 | 9 | 70.1 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m21-il | 200,000 | 5 | 73.7 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m21-il | 500,000 | 9 | 107.3 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m21-il | 500,000 | 5 | 105.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m21-il | 1,000,000 | 9 | 135.9 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m21-il | 1,000,000 | 5 | 128.4 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx38153-il | 50,000 | 9 | 31.2 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx38153-il | 50,000 | 5 | 26.6 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx38153-il | 100,000 | 9 | 46.9 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx38153-il | 100,000 | 5 | 36.1 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx38153-il | 200,000 | 9 | 46.6 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx38153-il | 200,000 | 5 | 47.4 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx38153-il | 500,000 | 9 | 63.3 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx38153-il | 500,000 | 5 | 60.8 at α=1° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx38153-il | 1,000,000 | 9 | 91.5 at α=0.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx38153-il | 1,000,000 | 5 | 64.3 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag10-il | 50,000 | 9 | 31.2 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag10-il | 50,000 | 5 | 31 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag10-il | 100,000 | 9 | 41.2 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag10-il | 100,000 | 5 | 41.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag10-il | 200,000 | 9 | 52.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag10-il | 200,000 | 5 | 52.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag10-il | 500,000 | 9 | 69.8 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag10-il | 500,000 | 5 | 67.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag10-il | 1,000,000 | 9 | 81.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag10-il | 1,000,000 | 5 | 79.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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