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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(naca664221-il) NACA 66(4)-221 | NACA 66(4)-221 airfoil Max thickness 21% at 45% chord Max camber 1.1% at 50% chord | Remove Airfoil details Airfoil plotter |
(mh62-il) MH 62 9.3% | Martin Hepperle MH 62 for flying wings Max thickness 9.3% at 26.9% chord Max camber 1.6% at 36.6% chord | Remove Airfoil details Airfoil plotter |
(nl722343-il) NLR-7223-43 AIRFOIL | NLR NLR-7223-43 transonic rotorcraft airfoil Max thickness 8.6% at 38% chord Max camber 1.3% at 74% chord | Remove Airfoil details Airfoil plotter |
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Polars for (naca664221-il,mh62-il,nl722343-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca664221-il | 50,000 | 9 | 16.5 at α=12.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca664221-il | 50,000 | 5 | 12.2 at α=11.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca664221-il | 100,000 | 9 | 19.1 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca664221-il | 100,000 | 5 | 18.1 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca664221-il | 200,000 | 9 | 29.6 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca664221-il | 200,000 | 5 | 30.5 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca664221-il | 500,000 | 9 | 68.6 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca664221-il | 500,000 | 5 | 69.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca664221-il | 1,000,000 | 9 | 100.8 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca664221-il | 1,000,000 | 5 | 91.7 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh62-il | 50,000 | 9 | 28.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh62-il | 50,000 | 5 | 33.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh62-il | 100,000 | 9 | 45 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh62-il | 100,000 | 5 | 46 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh62-il | 200,000 | 9 | 60.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh62-il | 200,000 | 5 | 58.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh62-il | 500,000 | 9 | 80.5 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh62-il | 500,000 | 5 | 75 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh62-il | 1,000,000 | 9 | 94.6 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh62-il | 1,000,000 | 5 | 87.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nl722343-il | 50,000 | 9 | 30.4 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nl722343-il | 50,000 | 5 | 29.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nl722343-il | 100,000 | 9 | 42.5 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nl722343-il | 100,000 | 5 | 41.4 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nl722343-il | 200,000 | 9 | 53.6 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nl722343-il | 200,000 | 5 | 53.1 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nl722343-il | 500,000 | 9 | 70.2 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nl722343-il | 500,000 | 5 | 67.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nl722343-il | 1,000,000 | 9 | 82.6 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nl722343-il | 1,000,000 | 5 | 78.1 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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