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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(fx61147-il) FX 61-147 AIRFOIL | Wortmann FX 61-147 airfoil Max thickness 14.8% at 33.9% chord Max camber 3.2% at 33.9% chord | Remove Airfoil details Airfoil plotter |
(mh30-il) MH 30 7.84% | Martin Hepperle MH 30 for F3E and F3B Max thickness 7.8% at 31% chord Max camber 1.7% at 46.4% chord | Remove Airfoil details Airfoil plotter |
(goe207-il) GOE 207 (AVIATIK V8) AIRFOIL | Gottingen 207 (AVIATIK V8) airfoil Max thickness 8.8% at 19.9% chord Max camber 6.6% at 29.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (fx61147-il,mh30-il,goe207-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx61147-il | 50,000 | 9 | 8.4 at α=1° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx61147-il | 50,000 | 5 | 28.7 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx61147-il | 100,000 | 9 | 50 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx61147-il | 100,000 | 5 | 52.3 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx61147-il | 200,000 | 9 | 70.8 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx61147-il | 200,000 | 5 | 71.9 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx61147-il | 500,000 | 9 | 99.2 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx61147-il | 500,000 | 5 | 98.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx61147-il | 1,000,000 | 9 | 123.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx61147-il | 1,000,000 | 5 | 119.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh30-il | 50,000 | 9 | 34.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh30-il | 50,000 | 5 | 35.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh30-il | 100,000 | 9 | 51.2 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh30-il | 100,000 | 5 | 48.5 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh30-il | 200,000 | 9 | 67.1 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh30-il | 200,000 | 5 | 59.8 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh30-il | 500,000 | 9 | 85.1 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh30-il | 500,000 | 5 | 73.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh30-il | 1,000,000 | 9 | 95.5 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh30-il | 1,000,000 | 5 | 84.5 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe207-il | 50,000 | 9 | 20.8 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe207-il | 50,000 | 5 | 33.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe207-il | 100,000 | 9 | 47.4 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe207-il | 100,000 | 5 | 52 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe207-il | 200,000 | 9 | 70.4 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe207-il | 200,000 | 5 | 71.6 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe207-il | 500,000 | 9 | 99.1 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe207-il | 500,000 | 5 | 96.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe207-il | 1,000,000 | 9 | 120.2 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe207-il | 1,000,000 | 5 | 113.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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