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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(goe444-il) GOE 444 AIRFOIL | Gottingen 444 airfoil Max thickness 5.6% at 30% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(n2h15-il) NACA 2-H-15 AIRFOIL | NACA 2-H-15 rotorcraft airfoil Max thickness 14.7% at 40% chord Max camber 4.5% at 40% chord | Remove Airfoil details Airfoil plotter |
(hor04-il) ONERA HOR04 AIRFOIL | Onera propeller blade airfoils from US Patent 4 Max thickness 4.1% at 33.2% chord Max camber 1.4% at 38.3% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe444-il,n2h15-il,hor04-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe444-il | 50,000 | 9 | 17.1 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe444-il | 50,000 | 5 | 16.5 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe444-il | 100,000 | 9 | 21.5 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe444-il | 100,000 | 5 | 24.8 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe444-il | 200,000 | 9 | 38.2 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe444-il | 200,000 | 5 | 35.2 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe444-il | 500,000 | 9 | 45.9 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe444-il | 500,000 | 5 | 31.8 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe444-il | 1,000,000 | 9 | 42.3 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe444-il | 1,000,000 | 5 | 34.1 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n2h15-il | 50,000 | 9 | 18.1 at α=13° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n2h15-il | 50,000 | 5 | 13.4 at α=11.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n2h15-il | 100,000 | 9 | 20 at α=13.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n2h15-il | 100,000 | 5 | 20.3 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n2h15-il | 200,000 | 9 | 34.9 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n2h15-il | 200,000 | 5 | 38.1 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n2h15-il | 500,000 | 9 | 110.5 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n2h15-il | 500,000 | 5 | 107.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n2h15-il | 1,000,000 | 9 | 145.1 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n2h15-il | 1,000,000 | 5 | 122.1 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hor04-il | 50,000 | 9 | 28.1 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hor04-il | 50,000 | 5 | 32.3 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hor04-il | 100,000 | 9 | 45.2 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hor04-il | 100,000 | 5 | 40.3 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hor04-il | 200,000 | 9 | 54.8 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hor04-il | 200,000 | 5 | 46.2 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hor04-il | 500,000 | 9 | 61.2 at α=1.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hor04-il | 500,000 | 5 | 58.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hor04-il | 1,000,000 | 9 | 68.4 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hor04-il | 1,000,000 | 5 | 70.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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