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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(ag36-il) AG36 | Drela AG36 airfoil Max thickness 8.2% at 27.9% chord Max camber 2.3% at 37% chord | Remove Airfoil details Airfoil plotter |
(goe770-il) GOE 770 AIRFOIL | Gottingen 770 airfoil Max thickness 21% at 30% chord Max camber 4% at 30% chord | Remove Airfoil details Airfoil plotter |
(mh22-il) MH 22 7.2% | Martin Hepperle MH 22 for F3D Pylon Racing Max thickness 7.2% at 27% chord Max camber 1.8% at 37% chord | Remove Airfoil details Airfoil plotter |
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Polars for (ag36-il,goe770-il,mh22-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ag36-il | 50,000 | 9 | 32.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag36-il | 50,000 | 5 | 36.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag36-il | 100,000 | 9 | 50.2 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag36-il | 100,000 | 5 | 51 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag36-il | 200,000 | 9 | 67.5 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag36-il | 200,000 | 5 | 64.3 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag36-il | 500,000 | 9 | 88.9 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag36-il | 500,000 | 5 | 81 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag36-il | 1,000,000 | 9 | 103 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag36-il | 1,000,000 | 5 | 93 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe770-il | 50,000 | 9 | 2.9 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe770-il | 50,000 | 5 | 11.3 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe770-il | 100,000 | 9 | 19.2 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe770-il | 100,000 | 5 | 36.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe770-il | 200,000 | 9 | 53.6 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe770-il | 200,000 | 5 | 59.3 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe770-il | 500,000 | 9 | 87.7 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe770-il | 500,000 | 5 | 86.1 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe770-il | 1,000,000 | 9 | 112.7 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe770-il | 1,000,000 | 5 | 109 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh22-il | 50,000 | 9 | 33.8 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh22-il | 50,000 | 5 | 35 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh22-il | 100,000 | 9 | 48.5 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh22-il | 100,000 | 5 | 47.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh22-il | 200,000 | 9 | 63.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh22-il | 200,000 | 5 | 60.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh22-il | 500,000 | 9 | 82.8 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh22-il | 500,000 | 5 | 74.5 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh22-il | 1,000,000 | 9 | 92.7 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh22-il | 1,000,000 | 5 | 81.9 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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