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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(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 |
(goe383-il) GOE 383 AIRFOIL | Gottingen 383 airfoil Max thickness 20.2% at 28.7% chord Max camber 5% at 38.7% chord | Remove Airfoil details Airfoil plotter |
(goe510-il) GOE 510 AIRFOIL | Gottingen 510 airfoil Max thickness 13.7% at 19.7% chord Max camber 5.8% at 39.7% chord | Remove Airfoil details Airfoil plotter |
(mh200-il) MH 200 12.97% | Martin Hepperle MH 200 for a canard airplane (main wing) Max thickness 13% at 39.5% chord Max camber 2.1% at 49.8% chord | Remove Airfoil details Airfoil plotter |
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Polars for (mh82-il,goe383-il,goe510-il,mh200-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| 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 | |
| goe383-il | 50,000 | 9 | 3.6 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe383-il | 50,000 | 5 | 13.9 at α=0.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe383-il | 100,000 | 9 | 25 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe383-il | 100,000 | 5 | 40.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe383-il | 200,000 | 9 | 62.2 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe383-il | 200,000 | 5 | 60.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe383-il | 500,000 | 9 | 88.4 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe383-il | 500,000 | 5 | 83.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe383-il | 1,000,000 | 9 | 111.7 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe383-il | 1,000,000 | 5 | 106.1 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe510-il | 50,000 | 9 | 8.4 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe510-il | 50,000 | 5 | 29.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe510-il | 100,000 | 9 | 48.4 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe510-il | 100,000 | 5 | 48.1 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe510-il | 200,000 | 9 | 65.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe510-il | 200,000 | 5 | 61.6 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe510-il | 500,000 | 9 | 84.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe510-il | 500,000 | 5 | 82.4 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe510-il | 1,000,000 | 9 | 106.9 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe510-il | 1,000,000 | 5 | 99.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh200-il | 50,000 | 9 | 33.7 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh200-il | 50,000 | 5 | 32.3 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh200-il | 100,000 | 9 | 53.4 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh200-il | 100,000 | 5 | 51 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh200-il | 200,000 | 9 | 76.1 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh200-il | 200,000 | 5 | 66.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh200-il | 500,000 | 9 | 98.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh200-il | 500,000 | 5 | 85.7 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh200-il | 1,000,000 | 9 | 117 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh200-il | 1,000,000 | 5 | 93.7 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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