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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(goe188-il) GOE 188 (SCHTTE-LANZ 3U10) AIRFOIL | Gottingen 188 (Schatte-Lanz 3U10) airfoil Max thickness 8.9% at 30% chord Max camber 4.3% at 30% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe188-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe188-il | 50,000 | 9 | 31.6 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe188-il | 50,000 | 5 | 39.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe188-il | 100,000 | 9 | 51.4 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe188-il | 100,000 | 5 | 57.1 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe188-il | 200,000 | 9 | 71.1 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe188-il | 200,000 | 5 | 74.5 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe188-il | 500,000 | 9 | 98.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe188-il | 500,000 | 5 | 99 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe188-il | 1,000,000 | 9 | 119.1 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe188-il | 1,000,000 | 5 | 116.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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