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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(goe633-il) GOE 633 AIRFOIL | Gottingen 633 airfoil Max thickness 13.8% at 19.7% chord Max camber 4% at 39.7% chord | Remove Airfoil details Airfoil plotter |
(strand-il) STRAND AIRFOIL | Strand high lift airfoil Max thickness 15.4% at 26.1% chord Max camber 4.1% at 32.1% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe633-il,strand-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe633-il | 50,000 | 9 | 9.7 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe633-il | 50,000 | 5 | 26.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe633-il | 100,000 | 9 | 43.9 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe633-il | 100,000 | 5 | 48.9 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe633-il | 200,000 | 9 | 67.4 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe633-il | 200,000 | 5 | 66.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe633-il | 500,000 | 9 | 94.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe633-il | 500,000 | 5 | 90.8 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe633-il | 1,000,000 | 9 | 118.3 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe633-il | 1,000,000 | 5 | 102.6 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| strand-il | 50,000 | 9 | 5.7 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| strand-il | 50,000 | 5 | 8.5 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| strand-il | 100,000 | 9 | 7.5 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| strand-il | 100,000 | 5 | 14.2 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| strand-il | 200,000 | 9 | 15.5 at α=15.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| strand-il | 200,000 | 5 | 26.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| strand-il | 500,000 | 9 | 92.4 at α=13° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| strand-il | 500,000 | 5 | 101.6 at α=11.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| strand-il | 1,000,000 | 9 | 141.7 at α=11.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| strand-il | 1,000,000 | 5 | 147.1 at α=10.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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