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 | ||
(kenmar-il) KENNEDY AND MARSDEN AIRFOIL | University of Alberta/Kennedy and Marsden high lift airfoil Max thickness 27.9% at 31% chord Max camber 7.7% at 36.9% chord | Remove Airfoil details Airfoil plotter |
(kc135d-il) KC-135 BL351.6 AIRFOIL | Boeing KC-135 transonic airfoils Max thickness 9% at 40% chord Max camber 1.9% at 30% chord | Remove Airfoil details Airfoil plotter |
(goe676-il) GOE 676 (= M 12) AIRFOIL | Gottingen 676 (= M 12) airfoil Max thickness 11.9% at 30% chord Max camber 2% at 30% chord | Remove Airfoil details Airfoil plotter |
(e379-il) EPPLER 379 AIRFOIL | Eppler E379 ultralight airfoil Max thickness 2.2% at 5.8% chord Max camber 8% at 31.8% chord | Remove Airfoil details Airfoil plotter |
(vr12-il) BOEING-VERTOL VR-12 AIRFOIL | Boeing-Vertol/Dadone VR-12 rotorcraft airfoil Max thickness 10.6% at 35% chord Max camber 2.3% at 20% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (kenmar-il,kc135d-il,goe676-il,e379-il,vr12-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| kenmar-il | 50,000 | 9 | 3 at α=16° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kenmar-il | 50,000 | 5 | 3.5 at α=15° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kenmar-il | 100,000 | 9 | 3 at α=14° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kenmar-il | 100,000 | 5 | 4.7 at α=-8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kenmar-il | 200,000 | 9 | 5.1 at α=-7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kenmar-il | 200,000 | 5 | 17.1 at α=-0.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kenmar-il | 500,000 | 9 | 28.3 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kenmar-il | 500,000 | 5 | 59 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kenmar-il | 1,000,000 | 9 | 70.1 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kenmar-il | 1,000,000 | 5 | 97.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135d-il | 50,000 | 9 | 36.2 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135d-il | 50,000 | 5 | 36.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135d-il | 100,000 | 9 | 54.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135d-il | 100,000 | 5 | 52.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135d-il | 200,000 | 9 | 74.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135d-il | 200,000 | 5 | 68.8 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135d-il | 500,000 | 9 | 100.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135d-il | 500,000 | 5 | 84 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135d-il | 1,000,000 | 9 | 114.9 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135d-il | 1,000,000 | 5 | 86.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe676-il | 50,000 | 9 | 30.7 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe676-il | 50,000 | 5 | 33.6 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe676-il | 100,000 | 9 | 48.8 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe676-il | 100,000 | 5 | 48.8 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe676-il | 200,000 | 9 | 65.5 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe676-il | 200,000 | 5 | 62.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe676-il | 500,000 | 9 | 86.1 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe676-il | 500,000 | 5 | 77.7 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe676-il | 1,000,000 | 9 | 97.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe676-il | 1,000,000 | 5 | 85.9 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e379-il | 50,000 | 9 | 23.2 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e379-il | 50,000 | 5 | 40.6 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e379-il | 100,000 | 9 | 74.6 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e379-il | 100,000 | 5 | 66.8 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e379-il | 200,000 | 9 | 117.8 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e379-il | 200,000 | 5 | 91.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e379-il | 500,000 | 9 | 128 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e379-il | 500,000 | 5 | 118.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e379-il | 1,000,000 | 0 | 135.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr12-il | 50,000 | 9 | 28.9 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr12-il | 50,000 | 5 | 28.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr12-il | 100,000 | 9 | 39.4 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr12-il | 100,000 | 5 | 39.9 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr12-il | 200,000 | 9 | 49.2 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr12-il | 200,000 | 5 | 53.6 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr12-il | 500,000 | 9 | 73 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr12-il | 500,000 | 5 | 75.5 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr12-il | 1,000,000 | 9 | 94.4 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr12-il | 1,000,000 | 5 | 93.9 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||