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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(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 |
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Polars for (vr1-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| 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 | |
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