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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(goe611-il) GOE 611 AIRFOIL | Gottingen 611 airfoil Max thickness 12.9% at 29.9% chord Max camber 5.8% at 39.9% chord | Remove Airfoil details Airfoil plotter |
(mh82-il) MH 82 13.31% | Martin Hepperle MH 82 for flying wings (hang glider) Max thickness 13.3% at 24.6% chord Max camber 3.9% at 24.6% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe611-il,mh82-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe611-il | 50,000 | 9 | 10 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe611-il | 50,000 | 5 | 31.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe611-il | 100,000 | 9 | 52.7 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe611-il | 100,000 | 5 | 56.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe611-il | 200,000 | 9 | 77.3 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe611-il | 200,000 | 5 | 75.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe611-il | 500,000 | 9 | 106.6 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe611-il | 500,000 | 5 | 97 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe611-il | 1,000,000 | 9 | 125.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe611-il | 1,000,000 | 5 | 107.9 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh82-il | 50,000 | 9 | 11.1 at α=1.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh82-il | 50,000 | 5 | 23.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh82-il | 100,000 | 9 | 29.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh82-il | 100,000 | 5 | 42.1 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh82-il | 200,000 | 9 | 53.7 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh82-il | 200,000 | 5 | 61.7 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh82-il | 500,000 | 9 | 87.1 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh82-il | 500,000 | 5 | 90.5 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh82-il | 1,000,000 | 9 | 115.3 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh82-il | 1,000,000 | 5 | 115.2 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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