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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(mh121-il) MH 121 8.76% | Martin Hepperle MH 121 for tip section of a propeller Max thickness 8.8% at 37.9% chord Max camber 3% at 62.2% chord | Remove Airfoil details Airfoil plotter |
(naca644421-il) NACA 64(4)-421 | NACA 64(4)-421 airfoil Max thickness 20.9% at 34.8% chord Max camber 2.2% at 50% chord | Remove Airfoil details Airfoil plotter |
(fx601261-il) WORTMANN FX 60-126/1 AIRFOIL | Wortmann FX 60-126/1 airfoil Max thickness 12.6% at 27.9% chord Max camber 4% at 56.5% chord | Remove Airfoil details Airfoil plotter |
(e1098-il) EPPLER 1098 AIRFOIL | Eppler E1098 general aviation airfoil Max thickness 18.9% at 36.6% chord Max camber 3.7% at 54.5% chord | Remove Airfoil details Airfoil plotter |
(glennmartin3-il) Glenn Martin 3 | Glenn Martin 3 airfoil Max thickness 13.8% at 30% chord Max camber 4.6% at 30% chord | Remove Airfoil details Airfoil plotter |
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Polars for (mh121-il,naca644421-il,fx601261-il,e1098-il,glennmartin3-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| mh121-il | 50,000 | 9 | 31.9 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh121-il | 50,000 | 5 | 35.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh121-il | 100,000 | 9 | 53.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh121-il | 100,000 | 5 | 57.9 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh121-il | 200,000 | 9 | 84 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh121-il | 200,000 | 5 | 82.4 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh121-il | 500,000 | 9 | 125.8 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh121-il | 500,000 | 5 | 107.8 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh121-il | 1,000,000 | 9 | 139.1 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh121-il | 1,000,000 | 5 | 117.7 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca644421-il | 50,000 | 9 | 3.9 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca644421-il | 50,000 | 5 | 11.3 at α=14.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca644421-il | 100,000 | 9 | 21.9 at α=12.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca644421-il | 100,000 | 5 | 26.1 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca644421-il | 200,000 | 9 | 61.5 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca644421-il | 200,000 | 5 | 62.6 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca644421-il | 500,000 | 9 | 98.5 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca644421-il | 500,000 | 5 | 93.2 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca644421-il | 1,000,000 | 9 | 124.1 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca644421-il | 1,000,000 | 5 | 112.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx601261-il | 50,000 | 9 | 34.5 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx601261-il | 50,000 | 5 | 39.4 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx601261-il | 100,000 | 9 | 59.4 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx601261-il | 100,000 | 5 | 60.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx601261-il | 200,000 | 9 | 82.9 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx601261-il | 200,000 | 5 | 76.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx601261-il | 500,000 | 9 | 108.2 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx601261-il | 500,000 | 5 | 84.2 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx601261-il | 1,000,000 | 9 | 113.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx601261-il | 1,000,000 | 5 | 88.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1098-il | 50,000 | 9 | 5.3 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1098-il | 50,000 | 5 | 14.1 at α=13.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1098-il | 100,000 | 9 | 29.8 at α=12.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1098-il | 100,000 | 5 | 24.9 at α=11.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1098-il | 200,000 | 9 | 51.9 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1098-il | 200,000 | 5 | 63.7 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1098-il | 500,000 | 9 | 117.3 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1098-il | 500,000 | 5 | 112.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1098-il | 1,000,000 | 9 | 151.8 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1098-il | 1,000,000 | 5 | 139.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| glennmartin3-il | 50,000 | 9 | 32.5 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| glennmartin3-il | 50,000 | 5 | 29.1 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| glennmartin3-il | 100,000 | 9 | 41.6 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| glennmartin3-il | 100,000 | 5 | 38.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| glennmartin3-il | 200,000 | 9 | 54.8 at α=1° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| glennmartin3-il | 200,000 | 5 | 47.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| glennmartin3-il | 500,000 | 9 | 62.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| glennmartin3-il | 500,000 | 5 | 62.6 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| glennmartin3-il | 1,000,000 | 9 | 78.7 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| glennmartin3-il | 1,000,000 | 5 | 78.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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