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 |
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Polars for (vr13-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 | |
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