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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(goe433-il) GOE 433 AIRFOIL | Gottingen 433 airfoil Max thickness 17.4% at 29.2% chord Max camber 4.8% at 49.2% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe433-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe433-il | 50,000 | 9 | 5.7 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe433-il | 50,000 | 5 | 22.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe433-il | 100,000 | 9 | 48.2 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe433-il | 100,000 | 5 | 53.1 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe433-il | 200,000 | 9 | 75.9 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe433-il | 200,000 | 5 | 71.9 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe433-il | 500,000 | 9 | 102.7 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe433-il | 500,000 | 5 | 89 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe433-il | 1,000,000 | 9 | 115.9 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe433-il | 1,000,000 | 5 | 100.3 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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