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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(s1221-flap-il) S1221 w/ 4 deg flap | Selig S1221 airfoil with 4 deg flap Max thickness 12.1% at 21.8% chord Max camber 5.3% at 52.9% chord | Remove Airfoil details Airfoil plotter |
(usa35b-il) USA-35B AIRFOIL | USA-35B airfoil Max thickness 11.6% at 30% chord Max camber 4.1% at 40% chord | Remove Airfoil details Airfoil plotter |
(fx601001-il) FX 60-100 (126) AIRFOIL | Wortmann FX 60-100 (126) airfoil Max thickness 10.1% at 30.8% chord Max camber 3.6% at 59.7% chord | Remove Airfoil details Airfoil plotter |
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Polars for (s1221-flap-il,usa35b-il,fx601001-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s1221-flap-il | 50,000 | 9 | 31 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1221-flap-il | 50,000 | 5 | 39.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1221-flap-il | 100,000 | 9 | 48.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1221-flap-il | 100,000 | 5 | 56.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1221-flap-il | 200,000 | 9 | 69.3 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1221-flap-il | 200,000 | 5 | 76.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1221-flap-il | 500,000 | 9 | 104.6 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1221-flap-il | 500,000 | 5 | 106.5 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1221-flap-il | 1,000,000 | 9 | 133.8 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1221-flap-il | 1,000,000 | 5 | 129.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa35b-il | 50,000 | 9 | 24.6 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa35b-il | 50,000 | 5 | 36.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa35b-il | 100,000 | 9 | 53.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa35b-il | 100,000 | 5 | 56.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa35b-il | 200,000 | 9 | 76.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa35b-il | 200,000 | 5 | 75.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa35b-il | 500,000 | 9 | 106 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa35b-il | 500,000 | 5 | 97 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa35b-il | 1,000,000 | 9 | 125.6 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa35b-il | 1,000,000 | 5 | 113.1 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx601001-il | 50,000 | 9 | 38.3 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx601001-il | 50,000 | 5 | 42.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx601001-il | 100,000 | 9 | 61 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx601001-il | 100,000 | 5 | 62.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx601001-il | 200,000 | 9 | 84.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx601001-il | 200,000 | 5 | 76.8 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx601001-il | 500,000 | 9 | 103 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx601001-il | 500,000 | 5 | 92.4 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx601001-il | 1,000,000 | 9 | 116.1 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx601001-il | 1,000,000 | 5 | 101.4 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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