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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(goe645-il) GOE 645 AIRFOIL | Gottingen 645 airfoil Max thickness 15.4% at 19.4% chord Max camber 4.8% at 39.4% chord | Remove Airfoil details Airfoil plotter |
(n10-il) N-10 | N-10 airfoil Max thickness 11.2% at 30% chord Max camber 3.6% at 40% chord | Remove Airfoil details Airfoil plotter |
(n13-il) N-13 | N-13 airfoil Max thickness 11.8% at 30% chord Max camber 0.1% at 95% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe645-il,n10-il,n13-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe645-il | 50,000 | 9 | 9.5 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe645-il | 50,000 | 5 | 28.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe645-il | 100,000 | 9 | 43.7 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe645-il | 100,000 | 5 | 48.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe645-il | 200,000 | 9 | 66.3 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe645-il | 200,000 | 5 | 65.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe645-il | 500,000 | 9 | 93.5 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe645-il | 500,000 | 5 | 84.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe645-il | 1,000,000 | 9 | 110.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe645-il | 1,000,000 | 5 | 88.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n10-il | 50,000 | 9 | 28.8 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n10-il | 50,000 | 5 | 37.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n10-il | 100,000 | 9 | 52 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n10-il | 100,000 | 5 | 52.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n10-il | 200,000 | 9 | 68.6 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n10-il | 200,000 | 5 | 68.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n10-il | 500,000 | 9 | 95.3 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n10-il | 500,000 | 5 | 92 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n10-il | 1,000,000 | 9 | 115.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n10-il | 1,000,000 | 5 | 109.4 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n13-il | 50,000 | 9 | 29 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n13-il | 50,000 | 5 | 27.7 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n13-il | 100,000 | 9 | 41.3 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n13-il | 100,000 | 5 | 37.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n13-il | 200,000 | 9 | 49.4 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n13-il | 200,000 | 5 | 45.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n13-il | 500,000 | 9 | 60.2 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n13-il | 500,000 | 5 | 60.8 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n13-il | 1,000,000 | 9 | 73.1 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n13-il | 1,000,000 | 5 | 71 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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