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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(nlf0215f-il) NASA/LANGLEY NLF(1)-0215F AIRFOIL | NASA/Langley/Somers NLF(1)-0215F natural laminar flow airfoil Max thickness 15% at 37.7% chord Max camber 4% at 42.3% chord | Remove Airfoil details Airfoil plotter |
(s7055-il) S7055 (10.5%) Flat-Bottomed | Selig S7055 low Reynolds number airfoil Max thickness 10.5% at 31.8% chord Max camber 3.3% at 38.6% chord | Remove Airfoil details Airfoil plotter |
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Polars for (nlf0215f-il,s7055-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| nlf0215f-il | 50,000 | 9 | 25.9 at α=12.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlf0215f-il | 50,000 | 5 | 20.8 at α=11.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlf0215f-il | 100,000 | 9 | 46.8 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlf0215f-il | 100,000 | 5 | 49.4 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlf0215f-il | 200,000 | 9 | 76.3 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlf0215f-il | 200,000 | 5 | 76.9 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlf0215f-il | 500,000 | 9 | 110.8 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlf0215f-il | 500,000 | 5 | 108.9 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlf0215f-il | 1,000,000 | 9 | 139.7 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlf0215f-il | 1,000,000 | 5 | 131.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s7055-il | 50,000 | 9 | 31.1 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s7055-il | 50,000 | 5 | 36.2 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s7055-il | 100,000 | 9 | 54.3 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s7055-il | 100,000 | 5 | 56.6 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s7055-il | 200,000 | 9 | 77.3 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s7055-il | 200,000 | 5 | 75.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s7055-il | 500,000 | 9 | 107.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s7055-il | 500,000 | 5 | 99.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s7055-il | 1,000,000 | 9 | 129.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s7055-il | 1,000,000 | 5 | 116.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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