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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(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 |
(s8064-il) S8064 | Selig airfoil for Q-500 (Q500) pylon racing (12.33%). Used on the Great Planes Viper 500 ARF. Max thickness 12.3% at 37.8% chord Max camber 1.1% at 56.2% chord | Remove Airfoil details Airfoil plotter |
(goe55-il) GOE 55 AIRFOIL | Gottingen 55 airfoil Max thickness 6.2% at 14.9% chord Max camber 2% at 19.9% chord | Remove Airfoil details Airfoil plotter |
(nacam2-il) NACA M2 | NACA M2 airfoil Max thickness 8.1% at 30% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(goe564-il) GOE 564 AIRFOIL | Gottingen 564 airfoil Max thickness 8.2% at 30% chord Max camber 2.7% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe331-il,s8064-il,goe55-il,nacam2-il,goe564-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| 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 | |
| s8064-il | 50,000 | 9 | 31 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8064-il | 50,000 | 5 | 29.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s8064-il | 100,000 | 9 | 48.8 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8064-il | 100,000 | 5 | 46.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s8064-il | 200,000 | 9 | 68.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8064-il | 200,000 | 5 | 55.2 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s8064-il | 500,000 | 9 | 80.2 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8064-il | 500,000 | 5 | 65.4 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s8064-il | 1,000,000 | 9 | 90 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8064-il | 1,000,000 | 5 | 70.3 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe55-il | 50,000 | 9 | 26.3 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe55-il | 50,000 | 5 | 32.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe55-il | 100,000 | 9 | 42.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe55-il | 100,000 | 5 | 43.3 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe55-il | 200,000 | 9 | 54.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe55-il | 200,000 | 5 | 51.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe55-il | 500,000 | 9 | 64.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe55-il | 500,000 | 5 | 64.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe55-il | 1,000,000 | 9 | 72.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe55-il | 1,000,000 | 5 | 77.6 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacam2-il | 50,000 | 9 | 25.5 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam2-il | 50,000 | 5 | 23.6 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacam2-il | 100,000 | 9 | 33.2 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam2-il | 100,000 | 5 | 27.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacam2-il | 200,000 | 9 | 38.6 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam2-il | 200,000 | 5 | 36.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacam2-il | 500,000 | 9 | 44.5 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam2-il | 500,000 | 5 | 54.4 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacam2-il | 1,000,000 | 9 | 60.3 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam2-il | 1,000,000 | 5 | 70.5 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe564-il | 50,000 | 9 | 37.1 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe564-il | 50,000 | 5 | 37.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe564-il | 100,000 | 9 | 56 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe564-il | 100,000 | 5 | 52.6 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe564-il | 200,000 | 9 | 75.4 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe564-il | 200,000 | 5 | 65.6 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe564-il | 500,000 | 9 | 95.7 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe564-il | 500,000 | 5 | 77.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe564-il | 1,000,000 | 9 | 103.8 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe564-il | 1,000,000 | 5 | 89.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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