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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(la203a-il) DOUGLAS LA203A AIRFOIL | Douglas/Liebeck LA203A high lift airfoil Max thickness 15.7% at 34.3% chord Max camber 5.5% at 46% chord | Remove Airfoil details Airfoil plotter |
(n5h15-il) NACA 5-H-15 AIRFOIL | NACA 5-H-15 rotorcraft airfoil Max thickness 15.4% at 40% chord Max camber 2.9% at 30% chord | Remove Airfoil details Airfoil plotter |
(goe417-il) GOE 417 AIRFOIL | Gottingen 417 airfoil Max thickness 6% at 20% chord Max camber 6.1% at 40% chord | Remove Airfoil details Airfoil plotter |
(la2573a-il) LA2573A | Liebeck LA2573A airfoil Max thickness 13.7% at 28.8% chord Max camber 3.2% at 26.1% chord | Remove Airfoil details Airfoil plotter |
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Polars for (la203a-il,n5h15-il,goe417-il,la2573a-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| la203a-il | 50,000 | 9 | 6 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| la203a-il | 50,000 | 5 | 13.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| la203a-il | 100,000 | 9 | 30.6 at α=12.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| la203a-il | 100,000 | 5 | 46.5 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| la203a-il | 200,000 | 9 | 82.4 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| la203a-il | 200,000 | 5 | 85.4 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| la203a-il | 500,000 | 9 | 127.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| la203a-il | 500,000 | 5 | 124 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| la203a-il | 1,000,000 | 9 | 160.5 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| la203a-il | 1,000,000 | 5 | 151.5 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n5h15-il | 50,000 | 9 | 14.2 at α=14.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n5h15-il | 50,000 | 5 | 14.8 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n5h15-il | 100,000 | 9 | 30 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n5h15-il | 100,000 | 5 | 43.1 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n5h15-il | 200,000 | 9 | 70 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n5h15-il | 200,000 | 5 | 58.6 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n5h15-il | 500,000 | 9 | 78.2 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n5h15-il | 500,000 | 5 | 71.4 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n5h15-il | 1,000,000 | 9 | 92.8 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n5h15-il | 1,000,000 | 5 | 85.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe417-il | 50,000 | 9 | 38.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe417-il | 50,000 | 5 | 44.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe417-il | 100,000 | 9 | 62 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe417-il | 100,000 | 5 | 63.2 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe417-il | 200,000 | 9 | 82.8 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe417-il | 200,000 | 5 | 78.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe417-il | 500,000 | 9 | 105.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe417-il | 500,000 | 5 | 102.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe417-il | 1,000,000 | 9 | 127.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe417-il | 1,000,000 | 5 | 115.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| la2573a-il | 50,000 | 9 | 6.9 at α=-0.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| la2573a-il | 50,000 | 5 | 13.4 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| la2573a-il | 100,000 | 9 | 15.7 at α=14.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| la2573a-il | 100,000 | 5 | 27.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| la2573a-il | 200,000 | 9 | 62.3 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| la2573a-il | 200,000 | 5 | 64.9 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| la2573a-il | 500,000 | 9 | 102.6 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| la2573a-il | 500,000 | 5 | 95.3 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| la2573a-il | 1,000,000 | 9 | 125.8 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| la2573a-il | 1,000,000 | 5 | 110.9 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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