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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(vr7b-il) BOEING-VERTOL VR-7 AIRFOIL WITH TAB | Boeing-Vertol VR-7 rotorcraft airfoil with tab Max thickness 12% at 33% chord Max camber 3% at 29% chord | Remove Airfoil details Airfoil plotter |
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Polars for (vr7b-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| vr7b-il | 50,000 | 9 | 30.7 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr7b-il | 50,000 | 5 | 33.3 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr7b-il | 100,000 | 9 | 52.1 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr7b-il | 100,000 | 5 | 53.4 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr7b-il | 200,000 | 9 | 72.9 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr7b-il | 200,000 | 5 | 71.4 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr7b-il | 500,000 | 9 | 99.5 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr7b-il | 500,000 | 5 | 92.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr7b-il | 1,000,000 | 9 | 118.1 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr7b-il | 1,000,000 | 5 | 105.7 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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