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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(goe288-il) GOE 288 AIRFOIL | Gottingen 288 airfoil Max thickness 17.4% at 29.3% chord Max camber 5.5% at 39.3% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe288-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe288-il | 50,000 | 9 | 7.6 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe288-il | 50,000 | 5 | 27.4 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe288-il | 100,000 | 9 | 43.7 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe288-il | 100,000 | 5 | 50.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe288-il | 200,000 | 9 | 70.2 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe288-il | 200,000 | 5 | 69.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe288-il | 500,000 | 9 | 96.5 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe288-il | 500,000 | 5 | 91.5 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe288-il | 1,000,000 | 9 | 117.1 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe288-il | 1,000,000 | 5 | 113.9 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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