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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(goe134-il) GOE 134 (MVA H.12) AIRFOIL | Gottingen 134 (MVA H.12) airfoil Max thickness 9.5% at 30% chord Max camber 4% at 30% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe134-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe134-il | 50,000 | 9 | 29.4 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe134-il | 50,000 | 5 | 38.3 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe134-il | 100,000 | 9 | 50.7 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe134-il | 100,000 | 5 | 55.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe134-il | 200,000 | 9 | 70.4 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe134-il | 200,000 | 5 | 71.7 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe134-il | 500,000 | 9 | 96.1 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe134-il | 500,000 | 5 | 93.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe134-il | 1,000,000 | 9 | 114.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe134-il | 1,000,000 | 5 | 109.7 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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