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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(s1091-il) S1091 | Selig S1091 airfoil Max thickness 5.1% at 13.4% chord Max camber 5.7% at 45.1% chord | Remove Airfoil details Airfoil plotter |
(nacam2-il) NACA M2 | NACA M2 airfoil Max thickness 8.1% at 30% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(s4022-il) S4022 | Selig S4022 low Reynolds number airfoil Max thickness 11.3% at 34.1% chord Max camber 4.3% at 57.8% chord | Remove Airfoil details Airfoil plotter |
(fxs02196-il) FX S 02-196 AIRFOIL | Wortmann FX S 02-196 airfoil Max thickness 19.6% at 37.1% chord Max camber 3.7% at 43.5% chord | Remove Airfoil details Airfoil plotter |
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Polars for (s1091-il,nacam2-il,s4022-il,fxs02196-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s1091-il | 50,000 | 9 | 46.1 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1091-il | 50,000 | 5 | 48.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1091-il | 100,000 | 9 | 70.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1091-il | 100,000 | 5 | 69.9 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1091-il | 200,000 | 9 | 96.2 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1091-il | 200,000 | 5 | 90.7 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1091-il | 500,000 | 9 | 129.8 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1091-il | 500,000 | 5 | 111 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1091-il | 1,000,000 | 9 | 153 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1091-il | 1,000,000 | 5 | 117.7 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacam2-il | 50,000 | 9 | 25.5 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam2-il | 50,000 | 5 | 23.6 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacam2-il | 100,000 | 9 | 33.2 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam2-il | 100,000 | 5 | 27.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacam2-il | 200,000 | 9 | 38.6 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam2-il | 200,000 | 5 | 36.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacam2-il | 500,000 | 9 | 44.5 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam2-il | 500,000 | 5 | 54.4 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacam2-il | 1,000,000 | 9 | 60.3 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam2-il | 1,000,000 | 5 | 70.5 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4022-il | 50,000 | 9 | 39.4 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4022-il | 50,000 | 5 | 39.1 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4022-il | 100,000 | 9 | 64.7 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4022-il | 100,000 | 5 | 65.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4022-il | 200,000 | 9 | 93.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4022-il | 200,000 | 5 | 90.3 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4022-il | 500,000 | 9 | 129.8 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4022-il | 500,000 | 5 | 113.5 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4022-il | 1,000,000 | 9 | 148.3 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4022-il | 1,000,000 | 5 | 128.1 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fxs02196-il | 50,000 | 9 | 4.7 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fxs02196-il | 50,000 | 5 | 10.2 at α=13.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fxs02196-il | 100,000 | 9 | 16.8 at α=13.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fxs02196-il | 100,000 | 5 | 37.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fxs02196-il | 200,000 | 9 | 68.4 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fxs02196-il | 200,000 | 5 | 56 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fxs02196-il | 500,000 | 9 | 53.1 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fxs02196-il | 500,000 | 5 | 46.5 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fxs02196-il | 1,000,000 | 9 | 60.1 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fxs02196-il | 1,000,000 | 5 | 54.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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