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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(oaf117-il) OAF117 AIRFOIL | ONERA/Aerospatiale OAF117 Fenestron airfoil Max thickness 11.5% at 23.2% chord Max camber 2% at 46.9% chord | Remove Airfoil details Airfoil plotter |
(n66021-il) NACA 66-021 AIRFOIL | NACA 66(4)-021 airfoil Max thickness 21% at 45% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(fx76mp160-il) FX 76-MP-160 | Wortmann FX 76-MP-160 airfoil Max thickness 16.1% at 33.9% chord Max camber 6.1% at 50% chord | Remove Airfoil details Airfoil plotter |
(giiim-il) GIII BL430 AIRFOIL | Grumman/Gulfstream GIII transonic airfoils Max thickness 8.5% at 35.2% chord Max camber 1.9% at 25.2% chord | Remove Airfoil details Airfoil plotter |
(mh114-il) MH 114 13.02% | Martin Hepperle MH 114 for a propeller for ultralight Max thickness 13% at 28.1% chord Max camber 6.4% at 50% chord | Remove Airfoil details Airfoil plotter |
(goe505-il) GOE 505 AIRFOIL | Gottingen 505 airfoil Max thickness 14% at 19.7% chord Max camber 5.9% at 39.7% chord | Remove Airfoil details Airfoil plotter |
(goe57-il) GOE 57 AIRFOIL | Gottingen 57 airfoil Max thickness 6.3% at 19.9% chord Max camber 5.1% at 39.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (oaf117-il,n66021-il,fx76mp160-il,giiim-il,mh114-il,goe505-il,goe57-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| oaf117-il | 50,000 | 9 | 28.3 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf117-il | 50,000 | 5 | 34.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf117-il | 100,000 | 9 | 46.9 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf117-il | 100,000 | 5 | 49.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf117-il | 200,000 | 9 | 64.2 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf117-il | 200,000 | 5 | 63 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf117-il | 500,000 | 9 | 84.4 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf117-il | 500,000 | 5 | 78.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf117-il | 1,000,000 | 9 | 96.8 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf117-il | 1,000,000 | 5 | 89.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n66021-il | 50,000 | 9 | 18.6 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n66021-il | 50,000 | 5 | 11 at α=13.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n66021-il | 100,000 | 9 | 23.8 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n66021-il | 100,000 | 5 | 15.4 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n66021-il | 200,000 | 9 | 25.5 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n66021-il | 200,000 | 5 | 26.5 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n66021-il | 500,000 | 9 | 57.7 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n66021-il | 500,000 | 5 | 54.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n66021-il | 1,000,000 | 9 | 78.2 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n66021-il | 1,000,000 | 5 | 64.9 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx76mp160-il | 50,000 | 9 | 5.3 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx76mp160-il | 50,000 | 5 | 16.4 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx76mp160-il | 100,000 | 9 | 44.4 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx76mp160-il | 100,000 | 5 | 40.1 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx76mp160-il | 200,000 | 9 | 76.3 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx76mp160-il | 200,000 | 5 | 72 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx76mp160-il | 500,000 | 9 | 120.9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx76mp160-il | 500,000 | 5 | 109.3 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx76mp160-il | 1,000,000 | 9 | 152.5 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx76mp160-il | 1,000,000 | 5 | 110.6 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiim-il | 50,000 | 9 | 29.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiim-il | 50,000 | 5 | 31.3 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiim-il | 100,000 | 9 | 43.2 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiim-il | 100,000 | 5 | 41.4 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiim-il | 200,000 | 9 | 56.1 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiim-il | 200,000 | 5 | 52.2 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiim-il | 500,000 | 9 | 70.6 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiim-il | 500,000 | 5 | 70.5 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiim-il | 1,000,000 | 9 | 85.9 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiim-il | 1,000,000 | 5 | 85.7 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh114-il | 50,000 | 9 | 9.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh114-il | 50,000 | 5 | 26 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh114-il | 100,000 | 9 | 56.2 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh114-il | 100,000 | 5 | 60.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh114-il | 200,000 | 9 | 89.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh114-il | 200,000 | 5 | 88.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh114-il | 500,000 | 9 | 131.2 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh114-il | 500,000 | 5 | 121 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh114-il | 1,000,000 | 9 | 161 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh114-il | 1,000,000 | 5 | 140.6 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe505-il | 50,000 | 9 | 12.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe505-il | 50,000 | 5 | 29.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe505-il | 100,000 | 9 | 49.1 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe505-il | 100,000 | 5 | 43.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe505-il | 200,000 | 9 | 68.7 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe505-il | 200,000 | 5 | 53.8 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe505-il | 500,000 | 9 | 73.5 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe505-il | 500,000 | 5 | 69.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe505-il | 1,000,000 | 9 | 91 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe505-il | 1,000,000 | 5 | 87.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe57-il | 50,000 | 9 | 41.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe57-il | 50,000 | 5 | 43.5 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe57-il | 100,000 | 9 | 63.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe57-il | 100,000 | 5 | 59.2 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe57-il | 200,000 | 9 | 82.4 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe57-il | 200,000 | 5 | 70.2 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe57-il | 500,000 | 9 | 93 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe57-il | 500,000 | 5 | 86.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe57-il | 1,000,000 | 9 | 105.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe57-il | 1,000,000 | 5 | 102.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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