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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(fx08s176-il) WORTMANN FX 08-S-176 AIRFOIL | Wortmann FX 08-S-176 airfoil Max thickness 17.6% at 37.1% chord Max camber 5.7% at 37.1% chord | Remove Airfoil details Airfoil plotter |
(fx38153-il) FX 38-153 AIRFOIL | Wortmann FX 38-153 airfoil Max thickness 15.5% at 43.5% chord Max camber 2.1% at 80.4% chord | Remove Airfoil details Airfoil plotter |
(fx60126-il) WORTMANN FX 60-126 AIRFOIL | Wortmann FX 60-126 airfoil Max thickness 12.6% at 27.9% chord Max camber 3.6% at 56.5% chord | Remove Airfoil details Airfoil plotter |
(v43015-il) BOEING VERTOL V43015-2.48 AIRFOIL | Boeing-Vertol V43015-2.48 rotorcraft airfoil Max thickness 15% at 30% chord Max camber 3.7% at 15% 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 |
Drawing Options
Polars for (fx08s176-il,fx38153-il,fx60126-il,v43015-il,vr11x-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx08s176-il | 50,000 | 9 | 4.2 at α=13° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx08s176-il | 50,000 | 5 | 9.2 at α=-1.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx08s176-il | 100,000 | 9 | 5.1 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx08s176-il | 100,000 | 5 | 20.4 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx08s176-il | 200,000 | 9 | 29.1 at α=12.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx08s176-il | 200,000 | 5 | 50.8 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx08s176-il | 500,000 | 9 | 108.8 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx08s176-il | 500,000 | 5 | 106.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx08s176-il | 1,000,000 | 9 | 142 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx08s176-il | 1,000,000 | 5 | 139.3 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx38153-il | 50,000 | 9 | 31.2 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx38153-il | 50,000 | 5 | 26.6 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx38153-il | 100,000 | 9 | 46.9 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx38153-il | 100,000 | 5 | 36.1 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx38153-il | 200,000 | 9 | 46.6 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx38153-il | 200,000 | 5 | 47.4 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx38153-il | 500,000 | 9 | 63.3 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx38153-il | 500,000 | 5 | 60.8 at α=1° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx38153-il | 1,000,000 | 9 | 91.5 at α=0.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx38153-il | 1,000,000 | 5 | 64.3 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx60126-il | 50,000 | 9 | 34.4 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx60126-il | 50,000 | 5 | 39.1 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx60126-il | 100,000 | 9 | 57.6 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx60126-il | 100,000 | 5 | 58.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx60126-il | 200,000 | 9 | 79.7 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx60126-il | 200,000 | 5 | 75.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx60126-il | 500,000 | 9 | 104 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx60126-il | 500,000 | 5 | 88.4 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx60126-il | 1,000,000 | 9 | 112.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx60126-il | 1,000,000 | 5 | 95.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v43015-il | 50,000 | 9 | 23.5 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v43015-il | 50,000 | 5 | 27.1 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v43015-il | 100,000 | 9 | 36.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v43015-il | 100,000 | 5 | 39.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v43015-il | 200,000 | 9 | 51.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v43015-il | 200,000 | 5 | 53.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v43015-il | 500,000 | 9 | 74.6 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v43015-il | 500,000 | 5 | 76.7 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v43015-il | 1,000,000 | 9 | 98.2 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v43015-il | 1,000,000 | 5 | 95 at α=9.5° | 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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