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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(fx61168-il) FX 61-168 AIRFOIL | Wortmann FX 61-168 airfoil Max thickness 16.8% at 37.1% chord Max camber 3% at 37.1% chord | Remove Airfoil details Airfoil plotter |
(e854-il) EPPLER E854 AIRFOIL | Eppler E854 propeller airfoil Max thickness 13.4% at 32.3% chord Max camber 3.3% at 55.7% chord | Remove Airfoil details Airfoil plotter |
(eh2510-il) EH 2.5/10 | John Yost EH 2.5/10 for tailless R/C aircraft Max thickness 10% at 30% chord Max camber 2.5% at 25% chord | Remove Airfoil details Airfoil plotter |
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Polars for (fx61168-il,e854-il,eh2510-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx61168-il | 50,000 | 9 | 5.1 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx61168-il | 50,000 | 5 | 15.4 at α=12° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx61168-il | 100,000 | 9 | 44.7 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx61168-il | 100,000 | 5 | 48.4 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx61168-il | 200,000 | 9 | 71 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx61168-il | 200,000 | 5 | 73 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx61168-il | 500,000 | 9 | 104.5 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx61168-il | 500,000 | 5 | 101.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx61168-il | 1,000,000 | 9 | 129.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx61168-il | 1,000,000 | 5 | 120.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e854-il | 50,000 | 9 | 32.7 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e854-il | 50,000 | 5 | 31.8 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e854-il | 100,000 | 9 | 57.4 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e854-il | 100,000 | 5 | 58.1 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e854-il | 200,000 | 9 | 82.4 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e854-il | 200,000 | 5 | 80.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e854-il | 500,000 | 9 | 115.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e854-il | 500,000 | 5 | 103.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e854-il | 1,000,000 | 9 | 136.3 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e854-il | 1,000,000 | 5 | 117.5 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eh2510-il | 50,000 | 9 | 26.5 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eh2510-il | 50,000 | 5 | 30.9 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eh2510-il | 100,000 | 9 | 47 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eh2510-il | 100,000 | 5 | 48 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eh2510-il | 200,000 | 9 | 65.2 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eh2510-il | 200,000 | 5 | 56.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eh2510-il | 500,000 | 9 | 91.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eh2510-il | 500,000 | 5 | 62.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eh2510-il | 1,000,000 | 9 | 111.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eh2510-il | 1,000,000 | 5 | 71.3 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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