Airfoil Comparison
Select airfoils from the airfoil database or add your own airfoils and compare the airfoil shape and lift/drag polars.
| Open full size plan in new window | Open paginated plan in new window | |
| Download PDF file | SVG image as text file | |
| Clear all | ||
(goe611-il) GOE 611 AIRFOIL | Gottingen 611 airfoil Max thickness 12.9% at 29.9% chord Max camber 5.8% at 39.9% chord | Remove Airfoil details Airfoil plotter |
(fx2-il) WORTMANN FX 2 AIRFOIL | Wortmann FX 2 airfoil Max thickness 20.4% at 43.5% chord Max camber 3.8% at 69.1% chord | Remove Airfoil details Airfoil plotter |
(goe404-il) GOE 404 AIRFOIL | Gottingen 404 airfoil Max thickness 13.2% at 29.6% chord Max camber 5% at 29.6% chord | Remove Airfoil details Airfoil plotter |
(goe16k-il) GOE 16K AIRFOIL | Gottingen 16K airfoil Max thickness 18.2% at 50% chord Max camber 4.1% at 50% chord | Remove Airfoil details Airfoil plotter |
(e210-il) E210 (13.64%) | Eppler E210 low Reynolds number airfoil Max thickness 13.6% at 32.1% chord Max camber 3.7% at 50.7% chord | Remove Airfoil details Airfoil plotter |
(hobie-il) HOBIE | Hobie Hawk airfoil (Hobie Hawk R/C sailplane) Max thickness 8.5% at 25% chord Max camber 4% at 45% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (goe611-il,fx2-il,goe404-il,goe16k-il,e210-il,hobie-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe611-il | 50,000 | 9 | 10 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe611-il | 50,000 | 5 | 31.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe611-il | 100,000 | 9 | 52.7 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe611-il | 100,000 | 5 | 56.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe611-il | 200,000 | 9 | 77.3 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe611-il | 200,000 | 5 | 75.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe611-il | 500,000 | 9 | 106.6 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe611-il | 500,000 | 5 | 97 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe611-il | 1,000,000 | 9 | 125.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe611-il | 1,000,000 | 5 | 107.9 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx2-il | 50,000 | 9 | 18 at α=12.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx2-il | 50,000 | 5 | 14.9 at α=12.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx2-il | 100,000 | 9 | 23.7 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx2-il | 100,000 | 5 | 22.7 at α=11° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx2-il | 200,000 | 9 | 34.2 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx2-il | 200,000 | 5 | 34.1 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx2-il | 500,000 | 9 | 51.6 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx2-il | 500,000 | 5 | 50.5 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx2-il | 1,000,000 | 9 | 107.1 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx2-il | 1,000,000 | 5 | 111 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe404-il | 50,000 | 9 | 15.2 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe404-il | 50,000 | 5 | 31.6 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe404-il | 100,000 | 9 | 45.2 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe404-il | 100,000 | 5 | 50.8 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe404-il | 200,000 | 9 | 68.8 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe404-il | 200,000 | 5 | 69.7 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe404-il | 500,000 | 9 | 98.8 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe404-il | 500,000 | 5 | 94.2 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe404-il | 1,000,000 | 9 | 121.6 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe404-il | 1,000,000 | 5 | 110.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe16k-il | 50,000 | 9 | 21.5 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe16k-il | 50,000 | 5 | 16.6 at α=11.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe16k-il | 100,000 | 9 | 26.4 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe16k-il | 100,000 | 5 | 23.7 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe16k-il | 200,000 | 9 | 35.9 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe16k-il | 500,000 | 9 | 69.2 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe16k-il | 500,000 | 5 | 50.6 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe16k-il | 1,000,000 | 9 | 80.2 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe16k-il | 1,000,000 | 5 | 70.9 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e210-il | 50,000 | 9 | 9.8 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e210-il | 50,000 | 5 | 30.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e210-il | 100,000 | 9 | 52.7 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e210-il | 100,000 | 5 | 57.1 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e210-il | 200,000 | 9 | 78.7 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e210-il | 200,000 | 5 | 79.6 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e210-il | 500,000 | 9 | 113 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e210-il | 500,000 | 5 | 109 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e210-il | 1,000,000 | 9 | 140.3 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e210-il | 1,000,000 | 5 | 129.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hobie-il | 50,000 | 9 | 40.8 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hobie-il | 50,000 | 5 | 41.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hobie-il | 100,000 | 9 | 59.8 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hobie-il | 100,000 | 5 | 60.3 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hobie-il | 200,000 | 9 | 78.8 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hobie-il | 200,000 | 5 | 76.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hobie-il | 500,000 | 9 | 100.5 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hobie-il | 500,000 | 5 | 93 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hobie-il | 1,000,000 | 9 | 115.1 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hobie-il | 1,000,000 | 5 | 102.7 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||