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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(goe723-il) GOE 723 AIRFOIL | Gottingen 723 airfoil Max thickness 11.6% at 29.7% chord Max camber 4.5% at 49.7% chord | Remove Airfoil details Airfoil plotter |
(s822-nr) NREL's S822 Airfoil | NREL HAWT airfoil S822 tip 16.0% Dia=2 to 10 m Re=6.0E+5 Clmax(S)=1.00 Clmax(R)=0.98 Restrained max lift coef Max thickness 16% at 39.2% chord Max camber 1.8% at 59.5% chord | Remove Airfoil details Airfoil plotter |
(goe692-il) GOE 692 AIRFOIL | Gottingen 692 airfoil Max thickness 16.1% at 30% chord Max camber 5% at 40% chord | Remove Airfoil details Airfoil plotter |
(s1221-il) S1221 w/o flap | Selig S1221 airfoil Max thickness 12.1% at 21.8% chord Max camber 4.9% at 49.1% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe723-il,s822-nr,goe692-il,s1221-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe723-il | 50,000 | 9 | 32 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe723-il | 50,000 | 5 | 33.4 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe723-il | 100,000 | 9 | 58.4 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe723-il | 100,000 | 5 | 58.5 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe723-il | 200,000 | 9 | 82.2 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe723-il | 200,000 | 5 | 79.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe723-il | 500,000 | 9 | 114 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe723-il | 500,000 | 5 | 103.5 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe723-il | 1,000,000 | 9 | 136.6 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe723-il | 1,000,000 | 5 | 112 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s822-nr | 50,000 | 9 | 27.7 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s822-nr | 50,000 | 5 | 23.7 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s822-nr | 100,000 | 9 | 42.7 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s822-nr | 100,000 | 5 | 39.8 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s822-nr | 200,000 | 9 | 68.6 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s822-nr | 200,000 | 5 | 60.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s822-nr | 500,000 | 9 | 94.7 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s822-nr | 500,000 | 5 | 85.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s822-nr | 1,000,000 | 9 | 117.1 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s822-nr | 1,000,000 | 5 | 96.9 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe692-il | 50,000 | 9 | 7.3 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe692-il | 50,000 | 5 | 19 at α=10.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe692-il | 100,000 | 9 | 48.1 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe692-il | 100,000 | 5 | 49.6 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe692-il | 200,000 | 9 | 76.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe692-il | 200,000 | 5 | 73.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe692-il | 500,000 | 9 | 109 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe692-il | 500,000 | 5 | 99.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe692-il | 1,000,000 | 9 | 132.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe692-il | 1,000,000 | 5 | 114.5 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1221-il | 50,000 | 9 | 27.1 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1221-il | 50,000 | 5 | 36.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1221-il | 100,000 | 9 | 45.2 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1221-il | 100,000 | 5 | 54.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1221-il | 200,000 | 9 | 70 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1221-il | 200,000 | 5 | 76.5 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1221-il | 500,000 | 9 | 107.5 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1221-il | 500,000 | 5 | 110 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1221-il | 1,000,000 | 9 | 137.9 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1221-il | 1,000,000 | 5 | 135.1 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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