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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(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 |
(fx74cl5140-il) FX74_CL5_140 | Wortmann FX 74-CL5-140 high lift airfoil Max thickness 14% at 30.9% chord Max camber 9.9% at 37.1% chord | Remove Airfoil details Airfoil plotter |
(fx67k170-il) FX 67-K-170/17 AIRFOIL | Wortmann FX 67-K-170/17 airfoil Max thickness 17% at 40.2% chord Max camber 5.1% at 43.5% chord | Remove Airfoil details Airfoil plotter |
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Polars for (fx601001-il,fx74cl5140-il,fx67k170-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| 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 | |
| fx74cl5140-il | 50,000 | 9 | 6.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74cl5140-il | 50,000 | 5 | 18.3 at α=1° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74cl5140-il | 100,000 | 9 | 33.1 at α=0.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74cl5140-il | 100,000 | 5 | 46.8 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74cl5140-il | 200,000 | 9 | 72.7 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74cl5140-il | 200,000 | 5 | 73.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74cl5140-il | 500,000 | 9 | 118.8 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74cl5140-il | 500,000 | 5 | 115.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74cl5140-il | 1,000,000 | 9 | 156.9 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74cl5140-il | 1,000,000 | 5 | 149.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx67k170-il | 50,000 | 9 | 5 at α=11.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx67k170-il | 50,000 | 5 | 11.8 at α=14.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx67k170-il | 100,000 | 9 | 20.1 at α=13.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx67k170-il | 100,000 | 5 | 19.9 at α=12.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx67k170-il | 200,000 | 9 | 36.6 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx67k170-il | 200,000 | 5 | 48.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx67k170-il | 500,000 | 9 | 116.9 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx67k170-il | 500,000 | 5 | 111.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx67k170-il | 1,000,000 | 9 | 152.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx67k170-il | 1,000,000 | 5 | 141.3 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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