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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(mh84-il) MH 84 13.69% | Martin Hepperle MH 84 for flying wings (hang glider) Max thickness 13.7% at 21.5% chord Max camber 4.1% at 36.6% chord | Remove Airfoil details Airfoil plotter |
(naca001066-il) NACA 0010-66 | NACA 0010-66 airfoil Max thickness 10% at 60% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(as5046-il) AS5046 (16%) | AS5046 airfoil Ashok Gopalarathnam/Selig 16% airfoil Max thickness 16% at 37.6% chord Max camber 0.7% at 77.4% chord | Remove Airfoil details Airfoil plotter |
(goe416a-il) GOE 416A AIRFOIL | Gottingen 416A airfoil Max thickness 11.7% at 29.5% chord Max camber 1.3% at 59.6% chord | Remove Airfoil details Airfoil plotter |
(goe623-il) GOE 623 AIRFOIL | Gottingen 623 airfoil Max thickness 12% at 30% chord Max camber 3.8% at 40% chord | Remove Airfoil details Airfoil plotter |
(naca64210-il) NACA 64-210 | NACA 64-210 airfoil Max thickness 10% at 40% chord Max camber 1.1% at 50% chord | Remove Airfoil details Airfoil plotter |
(goe613-il) GOE 613 AIRFOIL | Gottingen 613 airfoil Max thickness 10.3% at 30% chord Max camber 4.1% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (mh84-il,naca001066-il,as5046-il,goe416a-il,goe623-il,naca64210-il,goe613-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| mh84-il | 50,000 | 9 | 15.2 at α=1.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh84-il | 50,000 | 5 | 30.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh84-il | 100,000 | 9 | 40.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh84-il | 100,000 | 5 | 48.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh84-il | 200,000 | 9 | 62.5 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh84-il | 200,000 | 5 | 66.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh84-il | 500,000 | 9 | 92.3 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh84-il | 500,000 | 5 | 92 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh84-il | 1,000,000 | 9 | 116.3 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh84-il | 1,000,000 | 5 | 113 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca001066-il | 50,000 | 9 | 20.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca001066-il | 50,000 | 5 | 21.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca001066-il | 100,000 | 9 | 26.6 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca001066-il | 100,000 | 5 | 28.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca001066-il | 200,000 | 9 | 33.9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca001066-il | 200,000 | 5 | 34.4 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca001066-il | 500,000 | 9 | 42.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca001066-il | 500,000 | 5 | 47.1 at α=10.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca001066-il | 1,000,000 | 9 | 53.6 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca001066-il | 1,000,000 | 5 | 59.7 at α=10.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| as5046-il | 50,000 | 9 | 28.2 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| as5046-il | 50,000 | 5 | 28.1 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| as5046-il | 100,000 | 9 | 42.2 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| as5046-il | 100,000 | 5 | 42.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| as5046-il | 200,000 | 9 | 58.1 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| as5046-il | 200,000 | 5 | 55.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| as5046-il | 500,000 | 9 | 77.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| as5046-il | 500,000 | 5 | 69.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| as5046-il | 1,000,000 | 9 | 90.8 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| as5046-il | 1,000,000 | 5 | 83.5 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe416a-il | 50,000 | 9 | 31.1 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe416a-il | 50,000 | 5 | 34 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe416a-il | 100,000 | 9 | 46.5 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe416a-il | 100,000 | 5 | 47.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe416a-il | 200,000 | 9 | 61.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe416a-il | 200,000 | 5 | 57.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe416a-il | 500,000 | 9 | 71 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe416a-il | 500,000 | 5 | 67.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe416a-il | 1,000,000 | 9 | 80.2 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe416a-il | 1,000,000 | 5 | 75.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe623-il | 50,000 | 9 | 27.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe623-il | 50,000 | 5 | 36 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe623-il | 100,000 | 9 | 53.5 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe623-il | 100,000 | 5 | 55 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe623-il | 200,000 | 9 | 75.4 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe623-il | 200,000 | 5 | 72.3 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe623-il | 500,000 | 9 | 102.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe623-il | 500,000 | 5 | 91.3 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe623-il | 1,000,000 | 9 | 120.6 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe623-il | 1,000,000 | 5 | 104.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca64210-il | 50,000 | 9 | 30.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca64210-il | 50,000 | 5 | 32.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca64210-il | 100,000 | 9 | 46.4 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca64210-il | 100,000 | 5 | 44.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca64210-il | 200,000 | 9 | 61.8 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca64210-il | 200,000 | 5 | 54 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca64210-il | 500,000 | 9 | 76.3 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca64210-il | 500,000 | 5 | 63.2 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca64210-il | 1,000,000 | 9 | 85.7 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca64210-il | 1,000,000 | 5 | 72.9 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe613-il | 50,000 | 9 | 30.3 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe613-il | 50,000 | 5 | 37 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe613-il | 100,000 | 9 | 53.3 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe613-il | 100,000 | 5 | 52.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe613-il | 200,000 | 9 | 72.3 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe613-il | 200,000 | 5 | 67.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe613-il | 500,000 | 9 | 93.8 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe613-il | 500,000 | 5 | 88.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe613-il | 1,000,000 | 9 | 112 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe613-il | 1,000,000 | 5 | 106 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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