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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(gs1-il) SIKORSKY GS-1 AIRFOIL | Gluharoff/Sikorsky GS-1 airfoil Max thickness 13.9% at 30% chord Max camber 4.1% at 50% chord | Remove Airfoil details Airfoil plotter |
(goe529-il) GOE 529 AIRFOIL | Gottingen 529 airfoil Max thickness 9.7% at 29.9% chord Max camber 5.8% at 39.9% chord | Remove Airfoil details Airfoil plotter |
(goe464-il) GOE 464 AIRFOIL | Gottingen 464 airfoil Max thickness 7.7% at 7.4% chord Max camber 9.9% at 29.9% chord | Remove Airfoil details Airfoil plotter |
(goe358-il) GOE 358 AIRFOIL | Gottingen 358 airfoil Max thickness 10.9% at 20% chord Max camber 5.6% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (gs1-il,goe529-il,goe464-il,goe358-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| gs1-il | 50,000 | 9 | 9.2 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| gs1-il | 50,000 | 5 | 29.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| gs1-il | 100,000 | 9 | 51 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| gs1-il | 100,000 | 5 | 54.1 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| gs1-il | 200,000 | 9 | 74.6 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| gs1-il | 200,000 | 5 | 74.4 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| gs1-il | 500,000 | 9 | 105.4 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| gs1-il | 500,000 | 5 | 100.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| gs1-il | 1,000,000 | 9 | 129.4 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| gs1-il | 1,000,000 | 5 | 119.8 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe529-il | 50,000 | 9 | 12.9 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe529-il | 50,000 | 5 | 33.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe529-il | 100,000 | 9 | 54.8 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe529-il | 100,000 | 5 | 60 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe529-il | 200,000 | 9 | 81.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe529-il | 200,000 | 5 | 81.9 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe529-il | 500,000 | 9 | 114.6 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe529-il | 500,000 | 5 | 109 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe529-il | 1,000,000 | 9 | 138.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe529-il | 1,000,000 | 5 | 127.3 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe464-il | 50,000 | 9 | 19.5 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe464-il | 50,000 | 5 | 37.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe464-il | 100,000 | 9 | 79.7 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe464-il | 100,000 | 5 | 56 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe464-il | 200,000 | 9 | 151.5 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe464-il | 200,000 | 5 | 72.4 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe464-il | 500,000 | 9 | 164.9 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe464-il | 500,000 | 5 | 97 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe464-il | 1,000,000 | 9 | 118.4 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe464-il | 1,000,000 | 5 | 117.3 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe358-il | 50,000 | 9 | 37.5 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe358-il | 50,000 | 5 | 42.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe358-il | 100,000 | 9 | 58.5 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe358-il | 100,000 | 5 | 61.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe358-il | 200,000 | 9 | 79 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe358-il | 200,000 | 5 | 79 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe358-il | 500,000 | 9 | 105.7 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe358-il | 500,000 | 5 | 99.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe358-il | 1,000,000 | 9 | 119.2 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe358-il | 1,000,000 | 5 | 115.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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