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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(nlf415-il) NASA/LANGLEY NLF(2)-0415 AIRFOIL | NASA/Langley-DFVLR/Somers(NASA)-Horstmann(DFVLR) NLF(2)-0415 natural laminar flow airfoil Max thickness 15% at 47.1% chord Max camber 3% at 71.4% chord | Remove Airfoil details Airfoil plotter |
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Polars for (nlf415-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| nlf415-il | 50,000 | 9 | 23.4 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlf415-il | 50,000 | 5 | 21.1 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlf415-il | 100,000 | 9 | 27.2 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlf415-il | 100,000 | 5 | 28.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlf415-il | 200,000 | 9 | 36.2 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlf415-il | 200,000 | 5 | 45.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlf415-il | 500,000 | 9 | 85.3 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlf415-il | 500,000 | 5 | 82.7 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlf415-il | 1,000,000 | 9 | 118.4 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlf415-il | 1,000,000 | 5 | 107.5 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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