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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(vr13-il) BOEING-VERTOL VR-13 AIRFOIL | Boeing-Vertol/Dadone VR-13 rotorcraft airfoil Max thickness 9.5% at 35% chord Max camber 2% at 20% chord | Remove Airfoil details Airfoil plotter |
(vr1-il) BOEING-VERTOL VR-1 AIRFOIL | Boeing-Vertol VR-1 rotorcraft airfoil Max thickness 11% at 35.3% chord Max camber 1.5% at 43.3% chord | Remove Airfoil details Airfoil plotter |
(vr8b-il) BOEING-VERTOL VR-8 AIRFOIL WITH TAB | Boeing-Vertol VR-8 rotorcraft airfoil with tab Max thickness 8.2% at 35% chord Max camber 1.2% at 35% chord | Remove Airfoil details Airfoil plotter |
(vr5-il) BOEING-VERTOL VR-5 AIRFOIL | Boeing-Vertol VR-5 rotorcraft airfoil Max thickness 12% at 35% chord Max camber 3.4% at 35% chord | Remove Airfoil details Airfoil plotter |
(dae51-il) DAE-51 AIRFOIL | Drela DAE51 low Reynolds number airfoil Max thickness 9.4% at 30.7% chord Max camber 4% at 46.4% chord | Remove Airfoil details Airfoil plotter |
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Polars for (vr13-il,vr1-il,vr8b-il,vr5-il,dae51-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| vr13-il | 50,000 | 9 | 29.1 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr13-il | 50,000 | 5 | 29.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr13-il | 100,000 | 9 | 40.1 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr13-il | 100,000 | 5 | 40 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr13-il | 200,000 | 9 | 49.6 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr13-il | 200,000 | 5 | 54.2 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr13-il | 500,000 | 9 | 74.5 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr13-il | 500,000 | 5 | 75.8 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr13-il | 1,000,000 | 9 | 94.6 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr13-il | 1,000,000 | 5 | 92.7 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr1-il | 50,000 | 9 | 30.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr1-il | 50,000 | 5 | 30 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr1-il | 100,000 | 9 | 46.9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr1-il | 100,000 | 5 | 44.1 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr1-il | 200,000 | 9 | 63.5 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr1-il | 200,000 | 5 | 53.6 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr1-il | 500,000 | 9 | 72.8 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr1-il | 500,000 | 5 | 61.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr1-il | 1,000,000 | 9 | 77.8 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr1-il | 1,000,000 | 5 | 75.6 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr8b-il | 50,000 | 9 | 32.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr8b-il | 50,000 | 5 | 31.7 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr8b-il | 100,000 | 9 | 41.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr8b-il | 100,000 | 5 | 37.1 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr8b-il | 200,000 | 9 | 47 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr8b-il | 200,000 | 5 | 44.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr8b-il | 500,000 | 9 | 84.8 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr8b-il | 500,000 | 5 | 50.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr8b-il | 1,000,000 | 9 | 64.1 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr8b-il | 1,000,000 | 5 | 62 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr5-il | 50,000 | 9 | 31.7 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr5-il | 50,000 | 5 | 29.5 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr5-il | 100,000 | 9 | 55.2 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr5-il | 100,000 | 5 | 55.4 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr5-il | 200,000 | 9 | 79.9 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr5-il | 200,000 | 5 | 78 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr5-il | 500,000 | 9 | 112.8 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr5-il | 500,000 | 5 | 105.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr5-il | 1,000,000 | 9 | 136.1 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr5-il | 1,000,000 | 5 | 117.3 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dae51-il | 50,000 | 9 | 39.3 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dae51-il | 50,000 | 5 | 41 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dae51-il | 100,000 | 9 | 62.6 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dae51-il | 100,000 | 5 | 63.3 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dae51-il | 200,000 | 9 | 87.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dae51-il | 200,000 | 5 | 84.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dae51-il | 500,000 | 9 | 121.2 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dae51-il | 500,000 | 5 | 110.3 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dae51-il | 1,000,000 | 9 | 144.4 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dae51-il | 1,000,000 | 5 | 127.2 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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