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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(goe804-il) GOE 804 (EA 8) AIRFOIL | Gottingen 804 (EA 8) airfoil Max thickness 6% at 40% chord Max camber 6.3% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe804-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe804-il | 50,000 | 9 | 43.7 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe804-il | 50,000 | 5 | 41.1 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe804-il | 100,000 | 9 | 70.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe804-il | 100,000 | 5 | 67.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe804-il | 200,000 | 9 | 107.1 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe804-il | 200,000 | 5 | 107 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe804-il | 500,000 | 9 | 169.1 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe804-il | 500,000 | 5 | 157.3 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe804-il | 1,000,000 | 9 | 211.4 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe804-il | 1,000,000 | 5 | 147 at α=0° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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