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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(goe436-il) GOE 436 AIRFOIL | Gottingen 436 airfoil Max thickness 11% at 30% chord Max camber 3.8% at 30% chord | Remove Airfoil details Airfoil plotter |
(naca16006-il) NACA 16-006 | NACA 16-006 airfoil Max thickness 6% at 50% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(naca651412-il) NACA 65(1)-412 | NACA 65(1)-412 airfoil Max thickness 12% at 39.9% chord Max camber 2.2% at 50% chord | Remove Airfoil details Airfoil plotter |
(naca001035-il) NACA 0010-35 | NACA 0010-35 airfoil Max thickness 10% at 50% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe436-il,naca16006-il,naca651412-il,naca001035-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe436-il | 50,000 | 9 | 23.5 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe436-il | 50,000 | 5 | 34.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe436-il | 100,000 | 9 | 47.8 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe436-il | 100,000 | 5 | 51.6 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe436-il | 200,000 | 9 | 68.2 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe436-il | 200,000 | 5 | 69.1 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe436-il | 500,000 | 9 | 96.7 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe436-il | 500,000 | 5 | 92.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe436-il | 1,000,000 | 9 | 118.3 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe436-il | 1,000,000 | 5 | 108.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16006-il | 50,000 | 9 | 16.4 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16006-il | 50,000 | 5 | 16.4 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16006-il | 100,000 | 9 | 20.6 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16006-il | 100,000 | 5 | 21.7 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16006-il | 200,000 | 9 | 25.6 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16006-il | 200,000 | 5 | 33.4 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16006-il | 500,000 | 9 | 41.2 at α=1.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16006-il | 500,000 | 5 | 34 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16006-il | 1,000,000 | 9 | 40.8 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16006-il | 1,000,000 | 5 | 36.2 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca651412-il | 50,000 | 9 | 28.3 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca651412-il | 50,000 | 5 | 30.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca651412-il | 100,000 | 9 | 53 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca651412-il | 100,000 | 5 | 51.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca651412-il | 200,000 | 9 | 74.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca651412-il | 200,000 | 5 | 67.9 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca651412-il | 500,000 | 9 | 98.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca651412-il | 500,000 | 5 | 88.8 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca651412-il | 1,000,000 | 9 | 116.3 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca651412-il | 1,000,000 | 5 | 100.9 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca001035-il | 50,000 | 9 | 17.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca001035-il | 50,000 | 5 | 18.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca001035-il | 100,000 | 9 | 24 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca001035-il | 100,000 | 5 | 27.1 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca001035-il | 200,000 | 9 | 37.4 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca001035-il | 200,000 | 5 | 32.2 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca001035-il | 500,000 | 9 | 39.6 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca001035-il | 500,000 | 5 | 36.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca001035-il | 1,000,000 | 9 | 43.2 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca001035-il | 1,000,000 | 5 | 45.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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