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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(goe802b-il) GOE 802 B AIRFOIL | Gottingen 802 B airfoil Max thickness 9.8% at 30% chord Max camber 6.1% at 40% chord | Remove Airfoil details Airfoil plotter |
(s1223-il) S1223 | Selig S1223 high lift low Reynolds number airfoil Max thickness 12.1% at 19.8% chord Max camber 8.1% at 49% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe802b-il,s1223-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe802b-il | 50,000 | 9 | 26.6 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe802b-il | 50,000 | 5 | 39.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe802b-il | 100,000 | 9 | 53.8 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe802b-il | 100,000 | 5 | 60.9 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe802b-il | 200,000 | 9 | 76.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe802b-il | 200,000 | 5 | 73.4 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe802b-il | 500,000 | 9 | 104.6 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe802b-il | 500,000 | 5 | 91 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe802b-il | 1,000,000 | 9 | 105.7 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe802b-il | 1,000,000 | 5 | 103.3 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1223-il | 50,000 | 9 | 33.1 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1223-il | 50,000 | 5 | 42.3 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1223-il | 100,000 | 9 | 54.5 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1223-il | 100,000 | 5 | 59.2 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1223-il | 200,000 | 9 | 73.6 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1223-il | 200,000 | 5 | 75.3 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1223-il | 500,000 | 9 | 98.8 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1223-il | 500,000 | 5 | 97.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1223-il | 1,000,000 | 9 | 121.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1223-il | 1,000,000 | 5 | 120 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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