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 | ||
(fx74080-il) WORTMANN FX 74-080 | Wortmann FX 74-080 airfoil Max thickness 8.2% at 43.5% chord Max camber 4.3% at 46.7% chord | Remove Airfoil details Airfoil plotter |
(goe287-il) GOE 287 AIRFOIL | Gottingen 287 airfoil Max thickness 8.9% at 29.9% chord Max camber 4.9% at 39.9% chord | Remove Airfoil details Airfoil plotter |
(goe478-il) GOE 478 AIRFOIL | Gottingen 478 airfoil Max thickness 13.4% at 29.6% chord Max camber 4.3% at 39.6% chord | Remove Airfoil details Airfoil plotter |
(goe481-il) GOE 481 AIRFOIL | Gottingen 481 airfoil Max thickness 13.4% at 9.6% chord Max camber 8.8% at 39.4% chord | Remove Airfoil details Airfoil plotter |
(ah81131-il) AH 81-131 | Althaus AH 81-131 airfoil Max thickness 13.1% at 40.2% chord Max camber 2.8% at 40.2% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (fx74080-il,goe287-il,goe478-il,goe481-il,ah81131-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx74080-il | 50,000 | 9 | 24.7 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74080-il | 50,000 | 5 | 27.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74080-il | 100,000 | 9 | 39.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74080-il | 100,000 | 5 | 58 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74080-il | 200,000 | 9 | 80.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74080-il | 200,000 | 5 | 87 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74080-il | 500,000 | 9 | 134.4 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74080-il | 500,000 | 5 | 131.5 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74080-il | 1,000,000 | 9 | 173.9 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74080-il | 1,000,000 | 5 | 164.5 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe287-il | 50,000 | 9 | 36.3 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe287-il | 50,000 | 5 | 38 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe287-il | 100,000 | 9 | 58.3 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe287-il | 100,000 | 5 | 59.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe287-il | 200,000 | 9 | 80 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe287-il | 200,000 | 5 | 77.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe287-il | 500,000 | 9 | 106.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe287-il | 500,000 | 5 | 94.5 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe287-il | 1,000,000 | 9 | 123 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe287-il | 1,000,000 | 5 | 106.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe478-il | 50,000 | 9 | 19.7 at α=12.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe478-il | 50,000 | 5 | 31.2 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe478-il | 100,000 | 9 | 51.6 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe478-il | 100,000 | 5 | 53 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe478-il | 200,000 | 9 | 73.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe478-il | 200,000 | 5 | 71 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe478-il | 500,000 | 9 | 101.3 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe478-il | 500,000 | 5 | 95.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe478-il | 1,000,000 | 9 | 125.5 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe478-il | 1,000,000 | 5 | 114.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe481-il | 50,000 | 9 | 7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe481-il | 50,000 | 5 | 28.9 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe481-il | 100,000 | 9 | 43 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe481-il | 100,000 | 5 | 41.1 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe481-il | 200,000 | 9 | 53.4 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe481-il | 200,000 | 5 | 48.9 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe481-il | 500,000 | 9 | 63.4 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe481-il | 500,000 | 5 | 58.3 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe481-il | 1,000,000 | 9 | 70.3 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe481-il | 1,000,000 | 5 | 63.8 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah81131-il | 50,000 | 9 | 23.4 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah81131-il | 50,000 | 5 | 21.5 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah81131-il | 100,000 | 9 | 37.5 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah81131-il | 100,000 | 5 | 38.1 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah81131-il | 200,000 | 9 | 72.2 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah81131-il | 200,000 | 5 | 70.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah81131-il | 500,000 | 9 | 110 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah81131-il | 500,000 | 5 | 95.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah81131-il | 1,000,000 | 9 | 126.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah81131-il | 1,000,000 | 5 | 104.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||