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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(mh84-il) MH 84 13.69% | Martin Hepperle MH 84 for flying wings (hang glider) Max thickness 13.7% at 21.5% chord Max camber 4.1% at 36.6% chord | Remove Airfoil details Airfoil plotter |
(e856-il) EPPLER 856 AIRFOIL | Eppler E856 propeller airfoil Max thickness 18.2% at 31.9% chord Max camber 4.2% at 50.2% chord | Remove Airfoil details Airfoil plotter |
(rhodesg32-il) Rhode St. Genese 32 | Rhode St. Genese 32 airfoil Max thickness 11.9% at 30% chord Max camber 3.9% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (mh84-il,e856-il,rhodesg32-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| mh84-il | 50,000 | 9 | 15.2 at α=1.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh84-il | 50,000 | 5 | 30.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh84-il | 100,000 | 9 | 40.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh84-il | 100,000 | 5 | 48.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh84-il | 200,000 | 9 | 62.5 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh84-il | 200,000 | 5 | 66.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh84-il | 500,000 | 9 | 92.3 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh84-il | 500,000 | 5 | 92 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh84-il | 1,000,000 | 9 | 116.3 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh84-il | 1,000,000 | 5 | 113 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e856-il | 50,000 | 9 | 4.6 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e856-il | 50,000 | 5 | 18.8 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e856-il | 100,000 | 9 | 28.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e856-il | 100,000 | 5 | 46.3 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e856-il | 200,000 | 9 | 64.8 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e856-il | 200,000 | 5 | 70.1 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e856-il | 500,000 | 9 | 100.8 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e856-il | 500,000 | 5 | 99.7 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e856-il | 1,000,000 | 9 | 128.9 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e856-il | 1,000,000 | 5 | 118.5 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rhodesg32-il | 50,000 | 9 | 24.3 at α=1° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rhodesg32-il | 50,000 | 5 | 33.4 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rhodesg32-il | 100,000 | 9 | 45.2 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rhodesg32-il | 100,000 | 5 | 48.3 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rhodesg32-il | 200,000 | 9 | 64.3 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rhodesg32-il | 200,000 | 5 | 64.9 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rhodesg32-il | 500,000 | 9 | 92.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rhodesg32-il | 500,000 | 5 | 89.7 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rhodesg32-il | 1,000,000 | 9 | 115 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rhodesg32-il | 1,000,000 | 5 | 108 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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