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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(nlf414f-il) NASA/LANGLEY NLF 0414F AIRFOIL | NASA/Langley/Viken NLF(1)-0414F natural laminar flow airfoil Max thickness 14.2% at 46.6% chord Max camber 2.4% at 53.7% chord | Remove Airfoil details Airfoil plotter |
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Polars for (nlf414f-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| nlf414f-il | 50,000 | 9 | 24.6 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlf414f-il | 50,000 | 5 | 23.5 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlf414f-il | 100,000 | 9 | 35.9 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlf414f-il | 100,000 | 5 | 34.4 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlf414f-il | 200,000 | 9 | 55.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlf414f-il | 200,000 | 5 | 53.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlf414f-il | 500,000 | 9 | 80.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlf414f-il | 500,000 | 5 | 77.1 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlf414f-il | 1,000,000 | 9 | 104.4 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlf414f-il | 1,000,000 | 5 | 95.4 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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