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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(mh91-il) MH 91 14.98% | Martin Hepperle MH 91 parafoil Max thickness 15% at 27.3% chord Max camber 1.4% at 18.7% chord | Remove Airfoil details Airfoil plotter |
(goe13k-il) GOE 13K AIRFOIL | Gottingen 13K airfoil Max thickness 14.8% at 50% chord Max camber 5.5% at 60% chord | Remove Airfoil details Airfoil plotter |
(mh95-il) MH 95 15.86% | Martin Hepperle MH 95 parafoil Max thickness 15.8% at 33.6% chord Max camber 0.9% at 81.6% chord | Remove Airfoil details Airfoil plotter |
(mh83-il) MH 83 13.29% | Martin Hepperle MH 83 for flying wings (hang glider) Max thickness 13.3% at 20.6% chord Max camber 4.5% at 32.6% chord | Remove Airfoil details Airfoil plotter |
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Polars for (mh91-il,goe13k-il,mh95-il,mh83-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| mh91-il | 50,000 | 9 | 16.1 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh91-il | 50,000 | 5 | 25.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh91-il | 100,000 | 9 | 34.3 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh91-il | 100,000 | 5 | 40.1 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh91-il | 200,000 | 9 | 52.7 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh91-il | 200,000 | 5 | 55.6 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh91-il | 500,000 | 9 | 78.1 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh91-il | 500,000 | 5 | 75.3 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh91-il | 1,000,000 | 9 | 96.6 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh91-il | 1,000,000 | 5 | 91.4 at α=10.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe13k-il | 50,000 | 9 | 25.6 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe13k-il | 50,000 | 5 | 20.9 at α=10.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe13k-il | 100,000 | 9 | 34.8 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe13k-il | 100,000 | 5 | 30.3 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe13k-il | 200,000 | 9 | 45.8 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe13k-il | 200,000 | 5 | 42.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe13k-il | 500,000 | 9 | 92.9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe13k-il | 500,000 | 5 | 85.8 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe13k-il | 1,000,000 | 9 | 129 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe13k-il | 1,000,000 | 5 | 93.9 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh95-il | 50,000 | 9 | 29.7 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh95-il | 50,000 | 5 | 29 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh95-il | 100,000 | 9 | 44.5 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh95-il | 100,000 | 5 | 37.4 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh95-il | 200,000 | 9 | 48.4 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh95-il | 200,000 | 5 | 45.6 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh95-il | 500,000 | 9 | 62.6 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh95-il | 500,000 | 5 | 60.8 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh95-il | 1,000,000 | 9 | 78 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh95-il | 1,000,000 | 5 | 74.3 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh83-il | 50,000 | 9 | 12.8 at α=1° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh83-il | 50,000 | 5 | 26.7 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh83-il | 100,000 | 9 | 34.1 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh83-il | 100,000 | 5 | 46.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh83-il | 200,000 | 9 | 59.1 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh83-il | 200,000 | 5 | 67.1 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh83-il | 500,000 | 9 | 94.1 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh83-il | 500,000 | 5 | 97.6 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh83-il | 1,000,000 | 9 | 123.8 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh83-il | 1,000,000 | 5 | 123.9 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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