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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(s806a-nr) NREL's S806A Airfoil (modified line 35) | NREL HAWT airfoil S806A tip Max thickness 11.5% at 45% chord Max camber 2.8% at 45% chord | Remove Airfoil details Airfoil plotter |
(sc20706-il) NASA SC(2)-0706 AIRFOIL | NASA SC(2)-0706 airfoil (NASA TP-2969) Max thickness 6% at 34% chord Max camber 1.6% at 82% chord | Remove Airfoil details Airfoil plotter |
(mh42-il) MH 42 8.94% | Martin Hepperle MH 42 low Reynolds number airfoil Max thickness 8.9% at 31.3% chord Max camber 1.8% at 36.3% chord | Remove Airfoil details Airfoil plotter |
(goe531-il) GOE 531 AIRFOIL | Gottingen 531 airfoil Max thickness 13.8% at 19.5% chord Max camber 14.7% at 49.3% chord | Remove Airfoil details Airfoil plotter |
(sc20404-il) NASA SC(2)-0404 AIRFOIL | NASA SC(2)-0404 airfoil (NASA TP-2969) Max thickness 4% at 37% chord Max camber 0.7% at 81% chord | Remove Airfoil details Airfoil plotter |
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Polars for (s806a-nr,sc20706-il,mh42-il,goe531-il,sc20404-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s806a-nr | 50,000 | 9 | 34.4 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s806a-nr | 100,000 | 9 | 53.3 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s806a-nr | 200,000 | 9 | 76.1 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s806a-nr | 500,000 | 9 | 107.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s806a-nr | 1,000,000 | 9 | 119.2 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20706-il | 50,000 | 9 | 24 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20706-il | 50,000 | 5 | 25.3 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20706-il | 100,000 | 9 | 38.2 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20706-il | 100,000 | 5 | 33.3 at α=1.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20706-il | 200,000 | 9 | 40.6 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20706-il | 200,000 | 5 | 44.1 at α=0.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20706-il | 500,000 | 9 | 67 at α=0.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20706-il | 500,000 | 5 | 55.8 at α=-0.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20706-il | 1,000,000 | 9 | 96.6 at α=-0.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20706-il | 1,000,000 | 5 | 68 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh42-il | 50,000 | 9 | 32.7 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh42-il | 50,000 | 5 | 35.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh42-il | 100,000 | 9 | 49.9 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh42-il | 100,000 | 5 | 49.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh42-il | 200,000 | 9 | 67 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh42-il | 200,000 | 5 | 62.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh42-il | 500,000 | 9 | 88.1 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh42-il | 500,000 | 5 | 78.5 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh42-il | 1,000,000 | 9 | 102 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh42-il | 1,000,000 | 5 | 89.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe531-il | 50,000 | 9 | 4.2 at α=16.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe531-il | 50,000 | 5 | 7.1 at α=18.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe531-il | 100,000 | 9 | 7.7 at α=19.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe531-il | 100,000 | 5 | 9.9 at α=18.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe531-il | 200,000 | 9 | 13.7 at α=19.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe531-il | 200,000 | 5 | 13.5 at α=17.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe531-il | 500,000 | 9 | 67.5 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe531-il | 500,000 | 5 | 66.1 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe531-il | 1,000,000 | 9 | 100.8 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe531-il | 1,000,000 | 5 | 86.7 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20404-il | 50,000 | 9 | 20.7 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20404-il | 50,000 | 5 | 19.1 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20404-il | 100,000 | 9 | 37.6 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20404-il | 100,000 | 5 | 26 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20404-il | 200,000 | 9 | 35.2 at α=1.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20404-il | 200,000 | 5 | 35.2 at α=1.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20404-il | 500,000 | 9 | 52 at α=1° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20404-il | 500,000 | 5 | 41.5 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20404-il | 1,000,000 | 9 | 49.7 at α=0.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20404-il | 1,000,000 | 5 | 55.1 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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