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 |
(nlr7301-il) NLR-7301 AIRFOIL | NLR NLR-7301 transonic airfoil Max thickness 16.5% at 35% chord Max camber 1.7% at 75% chord | Remove Airfoil details Airfoil plotter |
(nlf416-il) NASA/LANGLEY NLF(1)-0416 AIRFOIL | NASA/Langley/Somers NLF(1)-0416 natural laminar flow airfoil Max thickness 15.9% at 30.4% chord Max camber 2.5% at 34.8% chord | Remove Airfoil details Airfoil plotter |
(goe300-il) GOE 300 (FRIEDRICHSHAFEN G20) AIRFOIL | Gottingen 300 (Friedrichshafen G20) airfoil Max thickness 8.4% at 30% chord Max camber 6.7% at 30% chord | Remove Airfoil details Airfoil plotter |
(naca16021-il) NACA 16-021 | NACA 16-021 airfoil Max thickness 21% at 50% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (naca664221-il,nlr7301-il,nlf416-il,goe300-il,naca16021-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 | |
| nlr7301-il | 50,000 | 9 | 21 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlr7301-il | 50,000 | 5 | 18.7 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlr7301-il | 100,000 | 9 | 21.5 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlr7301-il | 100,000 | 5 | 26.7 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlr7301-il | 200,000 | 9 | 31 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlr7301-il | 200,000 | 5 | 37.2 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlr7301-il | 500,000 | 9 | 49.9 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlr7301-il | 500,000 | 5 | 55.4 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlr7301-il | 1,000,000 | 9 | 67.1 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlr7301-il | 1,000,000 | 5 | 70.2 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlf416-il | 50,000 | 9 | 14.8 at α=0.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlf416-il | 50,000 | 5 | 25.7 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlf416-il | 100,000 | 9 | 45.1 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlf416-il | 100,000 | 5 | 48.3 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlf416-il | 200,000 | 9 | 65.3 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlf416-il | 200,000 | 5 | 67.3 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlf416-il | 500,000 | 9 | 93.7 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlf416-il | 500,000 | 5 | 91.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlf416-il | 1,000,000 | 9 | 115.7 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlf416-il | 1,000,000 | 5 | 108.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe300-il | 50,000 | 9 | 19.9 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe300-il | 50,000 | 5 | 38.1 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe300-il | 100,000 | 9 | 54.9 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe300-il | 100,000 | 5 | 61 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe300-il | 200,000 | 9 | 79.1 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe300-il | 200,000 | 5 | 81.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe300-il | 500,000 | 9 | 107.6 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe300-il | 500,000 | 5 | 105.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe300-il | 1,000,000 | 9 | 130.4 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe300-il | 1,000,000 | 5 | 126.9 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16021-il | 50,000 | 9 | 21.9 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16021-il | 50,000 | 5 | 17.9 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16021-il | 100,000 | 9 | 28.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16021-il | 100,000 | 5 | 20.7 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16021-il | 200,000 | 9 | 33.7 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16021-il | 200,000 | 5 | 26.3 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16021-il | 500,000 | 9 | 39.5 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16021-il | 500,000 | 5 | 28.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16021-il | 1,000,000 | 9 | 42 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16021-il | 1,000,000 | 5 | 31.6 at α=12.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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