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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(naca001034-il) NACA 0010-34 | NACA 0010-34 airfoil Max thickness 10% at 40% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(eh1070-il) Eh 1.0/7.0 | John Yost EH 1.0/7.0 for tailless R/C aircraft Max thickness 7% at 28.7% chord Max camber 1% at 25.9% chord | Remove Airfoil details Airfoil plotter |
(goe331-il) GOE 331 (PFALZ 60) AIRFOIL | Gottingen 331 (Pfalz 60) airfoil Max thickness 10.6% at 29.9% chord Max camber 6.9% at 39.9% chord | Remove Airfoil details Airfoil plotter |
(e207-il) E207 (12.04%) | Eppler E207 low Reynolds number airfoil Max thickness 12% at 29.6% chord Max camber 2.5% at 38.6% chord | Remove Airfoil details Airfoil plotter |
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Polars for (naca001034-il,eh1070-il,goe331-il,e207-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca001034-il | 50,000 | 9 | 20.8 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca001034-il | 50,000 | 5 | 25.1 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca001034-il | 100,000 | 9 | 35.7 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca001034-il | 100,000 | 5 | 34.8 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca001034-il | 200,000 | 9 | 45.2 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca001034-il | 200,000 | 5 | 38.6 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca001034-il | 500,000 | 9 | 46.5 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca001034-il | 500,000 | 5 | 43.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca001034-il | 1,000,000 | 9 | 49.7 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca001034-il | 1,000,000 | 5 | 51.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eh1070-il | 50,000 | 9 | 30.2 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eh1070-il | 50,000 | 5 | 30.3 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eh1070-il | 100,000 | 9 | 41.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eh1070-il | 100,000 | 5 | 40.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eh1070-il | 200,000 | 9 | 52.4 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eh1070-il | 200,000 | 5 | 49.9 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eh1070-il | 500,000 | 9 | 67.1 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eh1070-il | 500,000 | 5 | 61.5 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eh1070-il | 1,000,000 | 9 | 77 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eh1070-il | 1,000,000 | 5 | 66.6 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe331-il | 50,000 | 9 | 22.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe331-il | 50,000 | 5 | 37.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe331-il | 100,000 | 9 | 58.8 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe331-il | 100,000 | 5 | 57.3 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe331-il | 200,000 | 9 | 79.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe331-il | 200,000 | 5 | 71.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe331-il | 500,000 | 9 | 97.1 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe331-il | 500,000 | 5 | 94.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe331-il | 1,000,000 | 9 | 119.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe331-il | 1,000,000 | 5 | 117.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e207-il | 50,000 | 9 | 30.9 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e207-il | 50,000 | 5 | 32.9 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e207-il | 100,000 | 9 | 52.3 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e207-il | 100,000 | 5 | 53.3 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e207-il | 200,000 | 9 | 73.8 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e207-il | 200,000 | 5 | 72.1 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e207-il | 500,000 | 9 | 102.7 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e207-il | 500,000 | 5 | 96.1 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e207-il | 1,000,000 | 9 | 124.7 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e207-il | 1,000,000 | 5 | 112.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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