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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(nlr1t-il) NLR-1T AIRFOIL | Bell/NASA/NLR NLR-1T rotorcraft airfoil Max thickness 8.7% at 38.3% chord Max camber 1.3% at 22.3% chord | Remove Airfoil details Airfoil plotter |
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Polars for (nlr1t-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| nlr1t-il | 50,000 | 9 | 29.6 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlr1t-il | 50,000 | 5 | 28.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlr1t-il | 100,000 | 9 | 38.9 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlr1t-il | 100,000 | 5 | 39.5 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlr1t-il | 200,000 | 9 | 53.4 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlr1t-il | 200,000 | 5 | 52 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlr1t-il | 500,000 | 9 | 70.5 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlr1t-il | 500,000 | 5 | 68.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlr1t-il | 1,000,000 | 9 | 84.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlr1t-il | 1,000,000 | 5 | 80.9 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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