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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(fx67k150-il) FX 67-K-150/17 AIRFOIL | Wortmann FX 67-K-150/17 airfoil Max thickness 15% at 40.2% chord Max camber 4.8% at 43.5% chord | Remove Airfoil details Airfoil plotter |
(fx73k170-il) FX 73-K-170/22 | Wortmann FX 73-K-170/22 airfoil for use with flaps (K) Max thickness 17.1% at 40.2% chord Max camber 4.6% at 56.5% chord | Remove Airfoil details Airfoil plotter |
(fx61140-il) FX 61-140 AIRFOIL | Wortmann FX 61-140 airfoil Max thickness 14% at 33.9% chord Max camber 2.5% at 30.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (fx67k150-il,fx73k170-il,fx61140-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx67k150-il | 50,000 | 9 | 5.8 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx67k150-il | 50,000 | 5 | 14.3 at α=12° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx67k150-il | 100,000 | 9 | 25 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx67k150-il | 100,000 | 5 | 27.1 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx67k150-il | 200,000 | 9 | 61.6 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx67k150-il | 200,000 | 5 | 68.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx67k150-il | 500,000 | 9 | 126.3 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx67k150-il | 500,000 | 5 | 118.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx67k150-il | 1,000,000 | 9 | 157.2 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx67k150-il | 1,000,000 | 5 | 147.8 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73k170-il | 50,000 | 9 | 5.2 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73k170-il | 50,000 | 5 | 13.3 at α=14.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73k170-il | 100,000 | 9 | 26.9 at α=12.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73k170-il | 100,000 | 5 | 26.3 at α=11° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73k170-il | 200,000 | 9 | 63 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73k170-il | 200,000 | 5 | 65.6 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73k170-il | 500,000 | 9 | 112.9 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73k170-il | 500,000 | 5 | 110 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73k170-il | 1,000,000 | 9 | 145.1 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73k170-il | 1,000,000 | 5 | 138 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx61140-il | 50,000 | 9 | 14.4 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx61140-il | 50,000 | 5 | 31.2 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx61140-il | 100,000 | 9 | 51.6 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx61140-il | 100,000 | 5 | 52 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx61140-il | 200,000 | 9 | 69.3 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx61140-il | 200,000 | 5 | 70.6 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx61140-il | 500,000 | 9 | 96.6 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx61140-il | 500,000 | 5 | 96.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx61140-il | 1,000,000 | 9 | 119 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx61140-il | 1,000,000 | 5 | 115.3 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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