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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(fx73cl2152-il) FX 73-CL2-152 | Wortmann FX 73-CL2-152 airfoil Max thickness 15.2% at 22.2% chord Max camber 6.6% at 43.5% chord | Remove Airfoil details Airfoil plotter |
(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 |
(fx74cl6140-il) FX 74-CL6-140 | Wortmann FX 74-CL6-140 airfoil Max thickness 14.1% at 30.9% chord Max camber 7.1% at 33.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (fx73cl2152-il,s1221-flap-il,fx74cl6140-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx73cl2152-il | 50,000 | 9 | 16.3 at α=0° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73cl2152-il | 50,000 | 5 | 32.6 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73cl2152-il | 100,000 | 9 | 41.3 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73cl2152-il | 100,000 | 5 | 52.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73cl2152-il | 200,000 | 9 | 66.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73cl2152-il | 200,000 | 5 | 74.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73cl2152-il | 500,000 | 9 | 104.2 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73cl2152-il | 500,000 | 5 | 107.8 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73cl2152-il | 1,000,000 | 9 | 136.2 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73cl2152-il | 1,000,000 | 5 | 135.3 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| 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 | |
| fx74cl6140-il | 50,000 | 9 | 5.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74cl6140-il | 50,000 | 5 | 18.9 at α=0.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74cl6140-il | 100,000 | 9 | 19.9 at α=-0.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74cl6140-il | 100,000 | 5 | 40.7 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74cl6140-il | 200,000 | 9 | 48.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74cl6140-il | 200,000 | 5 | 72 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74cl6140-il | 500,000 | 9 | 114.8 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74cl6140-il | 500,000 | 5 | 120.5 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74cl6140-il | 1,000,000 | 9 | 157.9 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74cl6140-il | 1,000,000 | 5 | 158.6 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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