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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(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 |
(goe12k-il) GOE 12K AIRFOIL | Gottingen 12K airfoil Max thickness 11.1% at 50% chord Max camber 4.1% at 60% chord | Remove Airfoil details Airfoil plotter |
(s6062-il) S6062 8% | Selig S6062 low Reynolds number airfoil Max thickness 7.9% at 29.4% chord Max camber 1.4% at 43.7% chord | Remove Airfoil details Airfoil plotter |
(sc21006-il) NASA SC(2)-1006 AIRFOIL | NASA SC(2)-1006 airfoil Max thickness 6% at 30% chord Max camber 2.6% at 73% chord | Remove Airfoil details Airfoil plotter |
(sd7084-il) SD7084 (9.6%) | Selig/Donovan SD7084 low Reynolds number airfoil Max thickness 9.6% at 29.5% chord Max camber 2.3% at 38.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (mh200-il,goe12k-il,s6062-il,sc21006-il,sd7084-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| 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 | |
| goe12k-il | 50,000 | 9 | 28.9 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe12k-il | 50,000 | 5 | 27.3 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe12k-il | 100,000 | 9 | 42.3 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe12k-il | 100,000 | 5 | 40.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe12k-il | 200,000 | 9 | 66.2 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe12k-il | 200,000 | 5 | 65.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe12k-il | 500,000 | 9 | 114 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe12k-il | 500,000 | 5 | 104.2 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe12k-il | 1,000,000 | 9 | 146.7 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe12k-il | 1,000,000 | 5 | 84.6 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s6062-il | 50,000 | 9 | 34.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s6062-il | 50,000 | 5 | 35.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s6062-il | 100,000 | 9 | 50.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s6062-il | 100,000 | 5 | 48.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s6062-il | 200,000 | 9 | 65.2 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s6062-il | 200,000 | 5 | 58.8 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s6062-il | 500,000 | 9 | 82 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s6062-il | 500,000 | 5 | 68.4 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s6062-il | 1,000,000 | 9 | 91 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s6062-il | 1,000,000 | 5 | 73.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc21006-il | 50,000 | 9 | 28.3 at α=1° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc21006-il | 50,000 | 5 | 29.8 at α=0.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc21006-il | 100,000 | 9 | 39.2 at α=0.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc21006-il | 100,000 | 5 | 48.9 at α=-0.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc21006-il | 200,000 | 9 | 66.5 at α=-0.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc21006-il | 200,000 | 5 | 61.3 at α=-1° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc21006-il | 500,000 | 9 | 101.9 at α=-1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc21006-il | 500,000 | 5 | 92 at α=-2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc21006-il | 1,000,000 | 9 | 130.4 at α=-2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc21006-il | 1,000,000 | 5 | 100.2 at α=-3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd7084-il | 50,000 | 9 | 31.3 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd7084-il | 50,000 | 5 | 35.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd7084-il | 100,000 | 9 | 49.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd7084-il | 100,000 | 5 | 49.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd7084-il | 200,000 | 9 | 65.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd7084-il | 200,000 | 5 | 63.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd7084-il | 500,000 | 9 | 87.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd7084-il | 500,000 | 5 | 83.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd7084-il | 1,000,000 | 9 | 104.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd7084-il | 1,000,000 | 5 | 98.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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