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 |
(clarym18-il) CLARK YM-18 AIRFOIL | CLARK YM18 airfoil Max thickness 18% at 29.6% chord Max camber 3.6% at 39.6% chord | Remove Airfoil details Airfoil plotter |
(goe16k-il) GOE 16K AIRFOIL | Gottingen 16K airfoil Max thickness 18.2% at 50% chord Max camber 4.1% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (nlf414f-il,clarym18-il,goe16k-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 | |
| clarym18-il | 50,000 | 9 | 7.6 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarym18-il | 50,000 | 5 | 25.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarym18-il | 100,000 | 9 | 43.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarym18-il | 100,000 | 5 | 43.3 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarym18-il | 200,000 | 9 | 60.9 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarym18-il | 200,000 | 5 | 56 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarym18-il | 500,000 | 9 | 77.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarym18-il | 500,000 | 5 | 73.5 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarym18-il | 1,000,000 | 9 | 96.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarym18-il | 1,000,000 | 5 | 93.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe16k-il | 50,000 | 9 | 21.5 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe16k-il | 50,000 | 5 | 16.6 at α=11.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe16k-il | 100,000 | 9 | 26.4 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe16k-il | 100,000 | 5 | 23.7 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe16k-il | 200,000 | 9 | 35.9 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe16k-il | 500,000 | 9 | 69.2 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe16k-il | 500,000 | 5 | 50.6 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe16k-il | 1,000,000 | 9 | 80.2 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe16k-il | 1,000,000 | 5 | 70.9 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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