Airfoil Comparison
Select airfoils from the airfoil database or add your own airfoils and compare the airfoil shape and lift/drag polars.
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(goe798-il) GOE 798 AIRFOIL | Gottingen 798 airfoil Max thickness 20% at 30% chord Max camber 6% at 40% chord | Remove Airfoil details Airfoil plotter |
(vr11x-il) BOEING-VERTOL VR-11X AIRFOIL | Boeing-Vertol/NASA/Dadone VR-11X transonic rotorcraft airfoil Max thickness 11% at 40% chord Max camber 2.4% at 25% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe798-il,vr11x-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe798-il | 50,000 | 9 | 3.8 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe798-il | 50,000 | 5 | 10.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe798-il | 100,000 | 9 | 20.6 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe798-il | 100,000 | 5 | 31.9 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe798-il | 200,000 | 9 | 65.7 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe798-il | 200,000 | 5 | 61.7 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe798-il | 500,000 | 9 | 98.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe798-il | 500,000 | 5 | 83.8 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe798-il | 1,000,000 | 9 | 120 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe798-il | 1,000,000 | 5 | 84.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr11x-il | 50,000 | 9 | 30.5 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr11x-il | 50,000 | 5 | 29.4 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr11x-il | 100,000 | 9 | 41 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr11x-il | 100,000 | 5 | 39.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr11x-il | 200,000 | 9 | 55.4 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr11x-il | 200,000 | 5 | 51.6 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr11x-il | 500,000 | 9 | 71.7 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr11x-il | 500,000 | 5 | 73.2 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr11x-il | 1,000,000 | 9 | 92.3 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr11x-il | 1,000,000 | 5 | 89.6 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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