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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(goe492-il) GOE 492 AIRFOIL | Gottingen 492 airfoil Max thickness 6.2% at 29.9% chord Max camber 3.4% at 49.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe492-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe492-il | 50,000 | 9 | 31.1 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe492-il | 50,000 | 5 | 39 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe492-il | 100,000 | 9 | 57.2 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe492-il | 100,000 | 5 | 57.4 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe492-il | 200,000 | 9 | 81.4 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe492-il | 200,000 | 5 | 78.6 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe492-il | 500,000 | 9 | 112 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe492-il | 500,000 | 5 | 99.4 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe492-il | 1,000,000 | 9 | 128.6 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe492-il | 1,000,000 | 5 | 95.5 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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