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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(naca662415-il) NACA 66(2)-415 | NACA 66(2)-415 airfoil Max thickness 15% at 45% chord Max camber 2.2% at 50% chord | Remove Airfoil details Airfoil plotter |
(naca4415-il) NACA 4415 | NACA 4415 airfoil Max thickness 15% at 30.9% chord Max camber 4% at 40.2% chord | Remove Airfoil details Airfoil plotter |
(naca16015-il) NACA 16-015 | NACA 16-015 airfoil Max thickness 15% at 50% chord Max camber 0% at 0% 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 |
(naca23015-il) NACA 23015 | NACA 23015 airfoil Max thickness 15% at 30% chord Max camber 1.8% at 15% chord | Remove Airfoil details Airfoil plotter |
(naca65410-il) NACA 65-410 | NACA 65-410 airfoil Max thickness 10% at 39.9% chord Max camber 2.2% at 50% chord | Remove Airfoil details Airfoil plotter |
(naca0008-il) NACA 0008 | NACA 0008 airfoil Max thickness 8% at 30% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (naca662415-il,naca4415-il,naca16015-il,naca16021-il,naca23015-il,naca65410-il,naca0008-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca662415-il | 50,000 | 9 | 21.9 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca662415-il | 50,000 | 5 | 21.4 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca662415-il | 100,000 | 9 | 33.5 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca662415-il | 100,000 | 5 | 32.7 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca662415-il | 200,000 | 9 | 55.4 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca662415-il | 200,000 | 5 | 55.3 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca662415-il | 500,000 | 9 | 94 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca662415-il | 500,000 | 5 | 89.2 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca662415-il | 1,000,000 | 9 | 120.8 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca662415-il | 1,000,000 | 5 | 107.6 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca4415-il | 50,000 | 9 | 7.4 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca4415-il | 50,000 | 5 | 27.4 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca4415-il | 100,000 | 9 | 48.4 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca4415-il | 100,000 | 5 | 50.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca4415-il | 200,000 | 9 | 71.1 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca4415-il | 200,000 | 5 | 68.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca4415-il | 500,000 | 9 | 97 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca4415-il | 500,000 | 5 | 90.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca4415-il | 1,000,000 | 9 | 119.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca4415-il | 1,000,000 | 5 | 109.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16015-il | 50,000 | 9 | 22.4 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16015-il | 50,000 | 5 | 21.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16015-il | 100,000 | 9 | 29.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16015-il | 100,000 | 5 | 28.1 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16015-il | 200,000 | 9 | 40.4 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16015-il | 200,000 | 5 | 32 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16015-il | 500,000 | 9 | 44.6 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16015-il | 500,000 | 5 | 39.7 at α=10.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16015-il | 1,000,000 | 9 | 50.5 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16015-il | 1,000,000 | 5 | 50.5 at α=10.75° | 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 | |
| naca23015-il | 50,000 | 9 | 21 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca23015-il | 50,000 | 5 | 27.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca23015-il | 100,000 | 9 | 33.7 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca23015-il | 100,000 | 5 | 39.1 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca23015-il | 200,000 | 9 | 48.4 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca23015-il | 200,000 | 5 | 52.6 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca23015-il | 500,000 | 9 | 72 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca23015-il | 500,000 | 5 | 74.8 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca23015-il | 1,000,000 | 9 | 91 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca23015-il | 1,000,000 | 5 | 91.3 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca65410-il | 50,000 | 9 | 28.7 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca65410-il | 50,000 | 5 | 35.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca65410-il | 100,000 | 9 | 52.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca65410-il | 100,000 | 5 | 52.6 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca65410-il | 200,000 | 9 | 75.2 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca65410-il | 200,000 | 5 | 68.7 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca65410-il | 500,000 | 9 | 97.8 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca65410-il | 500,000 | 5 | 87.5 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca65410-il | 1,000,000 | 9 | 114.4 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca65410-il | 1,000,000 | 5 | 98.9 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0008-il | 50,000 | 9 | 26.1 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0008-il | 50,000 | 5 | 24.6 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0008-il | 100,000 | 9 | 34.6 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0008-il | 100,000 | 5 | 30.4 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0008-il | 200,000 | 9 | 41.1 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0008-il | 200,000 | 5 | 38.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0008-il | 500,000 | 9 | 50.2 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0008-il | 500,000 | 5 | 56.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0008-il | 1,000,000 | 9 | 68.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0008-il | 1,000,000 | 5 | 69.9 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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