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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(mh61-il) MH 61 10.26% | Martin Hepperle MH 61 for flying wings Max thickness 10.2% at 27.6% chord Max camber 1.4% at 37.3% chord | Remove Airfoil details Airfoil plotter |
(s4062-il) S4062-095-87 | Selig S4062 low Reynolds number airfoil Max thickness 9.5% at 31.7% chord Max camber 4% at 50.4% chord | Remove Airfoil details Airfoil plotter |
(fx66h60-il) FX 66-H-60 | Wortmann FX 66-H-60 airfoil Max thickness 6% at 22.2% chord Max camber 1.7% at 17% chord | Remove Airfoil details Airfoil plotter |
(goe286-il) GOE 286 AIRFOIL | Gottingen 286 airfoil Max thickness 9.4% at 29.9% chord Max camber 4.1% at 29.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (mh61-il,s4062-il,fx66h60-il,goe286-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| mh61-il | 50,000 | 9 | 31.3 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh61-il | 50,000 | 5 | 33 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh61-il | 100,000 | 9 | 47.6 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh61-il | 100,000 | 5 | 47.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh61-il | 200,000 | 9 | 63.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh61-il | 200,000 | 5 | 60.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh61-il | 500,000 | 9 | 84.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh61-il | 500,000 | 5 | 76.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh61-il | 1,000,000 | 9 | 98 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh61-il | 1,000,000 | 5 | 86.6 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4062-il | 50,000 | 9 | 38.7 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4062-il | 50,000 | 5 | 38.4 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4062-il | 100,000 | 9 | 62.7 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4062-il | 100,000 | 5 | 61.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4062-il | 200,000 | 9 | 90.5 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4062-il | 200,000 | 5 | 86.3 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4062-il | 500,000 | 9 | 128.5 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4062-il | 500,000 | 5 | 114.5 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4062-il | 1,000,000 | 9 | 155 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4062-il | 1,000,000 | 5 | 131 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66h60-il | 50,000 | 9 | 28.6 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66h60-il | 50,000 | 5 | 29.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66h60-il | 100,000 | 9 | 37.9 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66h60-il | 100,000 | 5 | 40.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66h60-il | 200,000 | 9 | 51.3 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66h60-il | 200,000 | 5 | 51.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66h60-il | 500,000 | 9 | 69.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66h60-il | 500,000 | 5 | 67.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66h60-il | 1,000,000 | 9 | 84.1 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66h60-il | 1,000,000 | 5 | 76.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe286-il | 50,000 | 9 | 27.9 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe286-il | 50,000 | 5 | 37.6 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe286-il | 100,000 | 9 | 52.2 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe286-il | 100,000 | 5 | 54.5 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe286-il | 200,000 | 9 | 72.3 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe286-il | 200,000 | 5 | 65.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe286-il | 500,000 | 9 | 83.6 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe286-il | 500,000 | 5 | 78.8 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe286-il | 1,000,000 | 9 | 95.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe286-il | 1,000,000 | 5 | 89.9 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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