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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(goe584-il) GOE 584 AIRFOIL | Gottingen 584 airfoil Max thickness 12.7% at 30% chord Max camber 5% at 40% chord | Remove Airfoil details Airfoil plotter |
(mh122-il) MH 122 9.32% | Martin Hepperle MH 122 for tip section of a propeller Max thickness 9.3% at 37.6% chord Max camber 3.4% at 64.3% chord | Remove Airfoil details Airfoil plotter |
(naca653618-il) NACA 65(3)-618 | NACA 65(3)-618 airfoil Max thickness 18% at 39.8% chord Max camber 3.3% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe584-il,mh122-il,naca653618-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe584-il | 50,000 | 9 | 8.6 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe584-il | 50,000 | 5 | 26 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe584-il | 100,000 | 9 | 51.6 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe584-il | 100,000 | 5 | 55 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe584-il | 200,000 | 9 | 78.1 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe584-il | 200,000 | 5 | 77.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe584-il | 500,000 | 9 | 112.3 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe584-il | 500,000 | 5 | 106 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe584-il | 1,000,000 | 9 | 137.5 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe584-il | 1,000,000 | 5 | 126.1 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh122-il | 50,000 | 9 | 38 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh122-il | 50,000 | 5 | 38 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh122-il | 100,000 | 9 | 61.1 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh122-il | 100,000 | 5 | 58.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh122-il | 200,000 | 9 | 90.1 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh122-il | 200,000 | 5 | 87.6 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh122-il | 500,000 | 9 | 137.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh122-il | 500,000 | 5 | 114.9 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh122-il | 1,000,000 | 9 | 161.2 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh122-il | 1,000,000 | 5 | 125.1 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca653618-il | 50,000 | 9 | 17.8 at α=12.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca653618-il | 50,000 | 5 | 15.3 at α=12.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca653618-il | 100,000 | 9 | 27.8 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca653618-il | 100,000 | 5 | 29 at α=10.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca653618-il | 200,000 | 9 | 67.7 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca653618-il | 200,000 | 5 | 70.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca653618-il | 500,000 | 9 | 110.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca653618-il | 500,000 | 5 | 105.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca653618-il | 1,000,000 | 9 | 138.3 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca653618-il | 1,000,000 | 5 | 128.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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