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 | ||
(sc20518-il) NASA SC(2)-0518 AIRFOIL | NASA SC(2)-0518 airfoil (NASA TP-2969) Max thickness 18% at 35% chord Max camber 1.9% at 82% chord | Remove Airfoil details Airfoil plotter |
(goe571-il) GOE 571 AIRFOIL | Gottingen 571 airfoil Max thickness 24.9% at 29.4% chord Max camber 9.8% at 29.4% chord | Remove Airfoil details Airfoil plotter |
(goe630-il) GOE 630 AIRFOIL | Gottingen 630 airfoil Max thickness 12.6% at 29.8% chord Max camber 7.7% at 39.8% chord | Remove Airfoil details Airfoil plotter |
(sc20012-il) NASA SC(2)-0012 AIRFOIL | NASA SC(2)-0012 airfoil (NASA TP-2969) Max thickness 12% at 37% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(hs1712-il) HAM-STD HS1-712 AIRFOIL | HS1 family of prop airfoils from US Patent No. 4 Max thickness 12% at 36% chord Max camber 4.9% at 44% chord | Remove Airfoil details Airfoil plotter |
(mh81-il) MH 81 13% | Martin Hepperle MH 81 for flying wings (hang glider) Max thickness 12.9% at 25.4% chord Max camber 3.3% at 25.4% chord | Remove Airfoil details Airfoil plotter |
(v13006-il) BOEING VERTOL V13006-.7 AIRFOIL | Boeing-Vertol V13006-.7 rotorcraft airfoil Max thickness 6% at 30.2% chord Max camber 0.9% at 20.2% chord | Remove Airfoil details Airfoil plotter |
(mh18-il) MH 18 11.16% | Martin Hepperle MH 18 for F3D Pylon Racing Max thickness 11.1% at 36.8% chord Max camber 2.7% at 42.1% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (sc20518-il,goe571-il,goe630-il,sc20012-il,hs1712-il,mh81-il,v13006-il,mh18-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| sc20518-il | 50,000 | 9 | 26 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20518-il | 50,000 | 5 | 20.9 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20518-il | 100,000 | 9 | 25.9 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20518-il | 100,000 | 5 | 30.2 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20518-il | 200,000 | 9 | 36.5 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20518-il | 200,000 | 5 | 43.2 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20518-il | 500,000 | 9 | 59.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20518-il | 500,000 | 5 | 62.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20518-il | 1,000,000 | 9 | 77.3 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20518-il | 1,000,000 | 5 | 78.1 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe571-il | 50,000 | 9 | 3.7 at α=-12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe571-il | 50,000 | 5 | 5.7 at α=-7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe571-il | 100,000 | 9 | 8.1 at α=-8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe571-il | 100,000 | 5 | 8.6 at α=0.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe571-il | 200,000 | 9 | 33.1 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe571-il | 200,000 | 5 | 34 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe571-il | 500,000 | 9 | 56.1 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe571-il | 500,000 | 5 | 42.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe571-il | 1,000,000 | 9 | 62.8 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe571-il | 1,000,000 | 5 | 52.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe630-il | 50,000 | 9 | 7.1 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe630-il | 50,000 | 5 | 28.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe630-il | 100,000 | 9 | 48.4 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe630-il | 100,000 | 5 | 54.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe630-il | 200,000 | 9 | 74.9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe630-il | 200,000 | 5 | 73.5 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe630-il | 500,000 | 9 | 103.7 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe630-il | 500,000 | 5 | 99.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe630-il | 1,000,000 | 9 | 129 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe630-il | 1,000,000 | 5 | 123.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20012-il | 50,000 | 9 | 24.6 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20012-il | 50,000 | 5 | 23.6 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20012-il | 100,000 | 9 | 33.1 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20012-il | 100,000 | 5 | 29.7 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20012-il | 200,000 | 9 | 36 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20012-il | 200,000 | 5 | 39.9 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20012-il | 500,000 | 9 | 53.7 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20012-il | 500,000 | 5 | 58.6 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20012-il | 1,000,000 | 9 | 71.8 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20012-il | 1,000,000 | 5 | 72.9 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hs1712-il | 50,000 | 9 | 36.4 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hs1712-il | 50,000 | 5 | 38.3 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hs1712-il | 100,000 | 9 | 60.7 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hs1712-il | 100,000 | 5 | 58.4 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hs1712-il | 200,000 | 9 | 82.8 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hs1712-il | 200,000 | 5 | 74.7 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hs1712-il | 500,000 | 9 | 103.4 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hs1712-il | 500,000 | 5 | 83.5 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hs1712-il | 1,000,000 | 9 | 103.7 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hs1712-il | 1,000,000 | 5 | 89.7 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh81-il | 50,000 | 9 | 11.8 at α=1° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh81-il | 50,000 | 5 | 23 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh81-il | 100,000 | 9 | 28.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh81-il | 100,000 | 5 | 41 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh81-il | 200,000 | 9 | 52 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh81-il | 200,000 | 5 | 60.1 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh81-il | 500,000 | 9 | 85.1 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh81-il | 500,000 | 5 | 88.3 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh81-il | 1,000,000 | 9 | 112.7 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh81-il | 1,000,000 | 5 | 111.9 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v13006-il | 50,000 | 9 | 27.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v13006-il | 50,000 | 5 | 28.1 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v13006-il | 100,000 | 9 | 37.7 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v13006-il | 100,000 | 5 | 35.3 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v13006-il | 200,000 | 9 | 46.3 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v13006-il | 200,000 | 5 | 41.1 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v13006-il | 500,000 | 9 | 54.7 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v13006-il | 500,000 | 5 | 53.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v13006-il | 1,000,000 | 9 | 62.4 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v13006-il | 1,000,000 | 5 | 64.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh18-il | 50,000 | 9 | 32.3 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh18-il | 50,000 | 5 | 31.7 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh18-il | 100,000 | 9 | 53.3 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh18-il | 100,000 | 5 | 53.3 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh18-il | 200,000 | 9 | 77.2 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh18-il | 200,000 | 5 | 74.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh18-il | 500,000 | 9 | 108.6 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh18-il | 500,000 | 5 | 96.4 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh18-il | 1,000,000 | 9 | 127.4 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh18-il | 1,000,000 | 5 | 107.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||