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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(mh32-il) MH 32 8.7% | Martin Hepperle MH 32 for F3E and F3B Max thickness 8.7% at 30.2% chord Max camber 2.3% at 45.7% chord | Remove Airfoil details Airfoil plotter |
(goe331-il) GOE 331 (PFALZ 60) AIRFOIL | Gottingen 331 (Pfalz 60) airfoil Max thickness 10.6% at 29.9% chord Max camber 6.9% at 39.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (mh32-il,goe331-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| mh32-il | 50,000 | 9 | 35.2 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh32-il | 50,000 | 5 | 37.9 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh32-il | 100,000 | 9 | 53.9 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh32-il | 100,000 | 5 | 53.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh32-il | 200,000 | 9 | 72.3 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh32-il | 200,000 | 5 | 67.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh32-il | 500,000 | 9 | 94.7 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh32-il | 500,000 | 5 | 84 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh32-il | 1,000,000 | 9 | 109.3 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh32-il | 1,000,000 | 5 | 96.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe331-il | 50,000 | 9 | 22.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe331-il | 50,000 | 5 | 37.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe331-il | 100,000 | 9 | 58.8 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe331-il | 100,000 | 5 | 57.3 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe331-il | 200,000 | 9 | 79.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe331-il | 200,000 | 5 | 71.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe331-il | 500,000 | 9 | 97.1 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe331-il | 500,000 | 5 | 94.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe331-il | 1,000,000 | 9 | 119.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe331-il | 1,000,000 | 5 | 117.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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