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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(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 |
(sc20406-il) NASA SC(2)-0406 AIRFOIL | NASA SC(2)-0406 airfoil (NASA TP-2969) Max thickness 6% at 35% chord Max camber 0.6% at 79% chord | Remove Airfoil details Airfoil plotter |
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Polars for (fx73k170-il,sc20406-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| 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 | |
| sc20406-il | 50,000 | 9 | 20.9 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20406-il | 50,000 | 5 | 24.5 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20406-il | 100,000 | 9 | 37.2 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20406-il | 100,000 | 5 | 32.3 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20406-il | 200,000 | 9 | 47.5 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20406-il | 200,000 | 5 | 36.8 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20406-il | 500,000 | 9 | 52.9 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20406-il | 500,000 | 5 | 50.3 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20406-il | 1,000,000 | 9 | 59.8 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20406-il | 1,000,000 | 5 | 61.5 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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