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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(vr14-il) BOEING-VERTOL VR-14 AIRFOIL | Boeing-Vertol/Dadone VR-14 rotorcraft airfoil Max thickness 8% at 35% chord Max camber 1.7% at 20% chord | Remove Airfoil details Airfoil plotter |
(isa960-il) I.S.A. 960 | I.S.A. 960 airfoil Max thickness 9.5% at 30% chord Max camber 4.5% at 40% chord | Remove Airfoil details Airfoil plotter |
(rae5214-il) RAE 5214 AIRFOIL | RAE 5214 transonic airfoil Max thickness 9.7% at 35.5% chord Max camber 1.4% at 69.1% chord | Remove Airfoil details Airfoil plotter |
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Polars for (vr14-il,isa960-il,rae5214-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| vr14-il | 50,000 | 9 | 29.4 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr14-il | 50,000 | 5 | 29 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr14-il | 100,000 | 9 | 40.6 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr14-il | 100,000 | 5 | 40.3 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr14-il | 200,000 | 9 | 50.7 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr14-il | 200,000 | 5 | 54.3 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr14-il | 500,000 | 9 | 74.3 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr14-il | 500,000 | 5 | 73.4 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr14-il | 1,000,000 | 9 | 91.2 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr14-il | 1,000,000 | 5 | 87.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| isa960-il | 50,000 | 9 | 39.3 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| isa960-il | 50,000 | 5 | 38 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| isa960-il | 100,000 | 9 | 55.9 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| isa960-il | 100,000 | 5 | 49.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| isa960-il | 200,000 | 9 | 64.7 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| isa960-il | 200,000 | 5 | 53.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| isa960-il | 500,000 | 9 | 68.2 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| isa960-il | 500,000 | 5 | 72.1 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| isa960-il | 1,000,000 | 9 | 90.5 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| isa960-il | 1,000,000 | 5 | 91.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae5214-il | 50,000 | 9 | 29.2 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae5214-il | 50,000 | 5 | 27.5 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae5214-il | 100,000 | 9 | 40.3 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae5214-il | 100,000 | 5 | 35.7 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae5214-il | 200,000 | 9 | 46.4 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae5214-il | 200,000 | 5 | 49.1 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae5214-il | 500,000 | 9 | 66.6 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae5214-il | 500,000 | 5 | 68.4 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae5214-il | 1,000,000 | 9 | 83.3 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae5214-il | 1,000,000 | 5 | 80.7 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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