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 | ||
(raf25-il) RAF 25 AIRFOIL | RAF-25 airfoil Max thickness 6.5% at 29.9% chord Max camber 1% at 49.9% chord | Remove Airfoil details Airfoil plotter |
(s807-nr) NREL's S807 Airfoil | NREL HAWT airfoil S807 root Max thickness 18% at 28.7% chord Max camber 1.9% at 78.3% chord | Remove Airfoil details Airfoil plotter |
(goe592-il) GOE 592 AIRFOIL | Gottingen 592 airfoil Max thickness 14.3% at 29.7% chord Max camber 7.5% at 39.7% chord | Remove Airfoil details Airfoil plotter |
(ste87151-il) EPPLER STE 871-514 AIRFOIL | Eppler STE 871-514 airfoil Max thickness 13.9% at 47.3% chord Max camber 2.5% at 79% chord | Remove Airfoil details Airfoil plotter |
(mh32-il) MH 32 8.7% | Martin Hepperle MH 32 for F3E and F3B Max thickness 8.7% at 30.2% chord Max camber 2.3% at 45.7% chord | Remove Airfoil details Airfoil plotter |
(goe535-il) GOE 535 AIRFOIL | Gottingen 535 airfoil Max thickness 16.1% at 20% chord Max camber 5.8% at 50% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (raf25-il,s807-nr,goe592-il,ste87151-il,mh32-il,goe535-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| raf25-il | 50,000 | 9 | 28.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf25-il | 50,000 | 5 | 30.6 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf25-il | 100,000 | 9 | 43.3 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf25-il | 100,000 | 5 | 40.2 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf25-il | 200,000 | 9 | 56.2 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf25-il | 200,000 | 5 | 47.8 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf25-il | 500,000 | 9 | 68.2 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf25-il | 500,000 | 5 | 55.7 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf25-il | 1,000,000 | 9 | 72.2 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf25-il | 1,000,000 | 5 | 68.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s807-nr | 50,000 | 9 | 20.3 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s807-nr | 50,000 | 5 | 22 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s807-nr | 100,000 | 9 | 33.4 at α=12.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s807-nr | 100,000 | 5 | 40.3 at α=10.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s807-nr | 200,000 | 9 | 56.4 at α=11.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s807-nr | 200,000 | 5 | 59.4 at α=10.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s807-nr | 500,000 | 9 | 84.9 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s807-nr | 500,000 | 5 | 83.9 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s807-nr | 1,000,000 | 9 | 106.7 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s807-nr | 1,000,000 | 5 | 101.7 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe592-il | 50,000 | 9 | 5.3 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe592-il | 50,000 | 5 | 13.3 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe592-il | 100,000 | 9 | 32.1 at α=12.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe592-il | 100,000 | 5 | 45.9 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe592-il | 200,000 | 9 | 76.5 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe592-il | 200,000 | 5 | 76.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe592-il | 500,000 | 9 | 114.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe592-il | 500,000 | 5 | 107 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe592-il | 1,000,000 | 9 | 142.4 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe592-il | 1,000,000 | 5 | 124.5 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ste87151-il | 50,000 | 9 | 28 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ste87151-il | 50,000 | 5 | 25.8 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ste87151-il | 100,000 | 9 | 40.6 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ste87151-il | 100,000 | 5 | 36.4 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ste87151-il | 200,000 | 9 | 55.2 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ste87151-il | 200,000 | 5 | 52.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ste87151-il | 500,000 | 9 | 81.8 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ste87151-il | 500,000 | 5 | 79.1 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ste87151-il | 1,000,000 | 9 | 113.9 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ste87151-il | 1,000,000 | 5 | 104.5 at α=1.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh32-il | 50,000 | 9 | 35.2 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh32-il | 50,000 | 5 | 37.9 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh32-il | 100,000 | 9 | 53.9 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh32-il | 100,000 | 5 | 53.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh32-il | 200,000 | 9 | 72.3 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh32-il | 200,000 | 5 | 67.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh32-il | 500,000 | 9 | 94.7 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh32-il | 500,000 | 5 | 84 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh32-il | 1,000,000 | 9 | 109.3 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh32-il | 1,000,000 | 5 | 96.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe535-il | 50,000 | 9 | 7.2 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe535-il | 50,000 | 5 | 29.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe535-il | 100,000 | 9 | 43.1 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe535-il | 100,000 | 5 | 50.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe535-il | 200,000 | 9 | 68.1 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe535-il | 200,000 | 5 | 68.5 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe535-il | 500,000 | 9 | 96.6 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe535-il | 500,000 | 5 | 90.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe535-il | 1,000,000 | 9 | 116.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe535-il | 1,000,000 | 5 | 110.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||