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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(fx601261-il) WORTMANN FX 60-126/1 AIRFOIL | Wortmann FX 60-126/1 airfoil Max thickness 12.6% at 27.9% chord Max camber 4% at 56.5% chord | Remove Airfoil details Airfoil plotter |
(nlf416-il) NASA/LANGLEY NLF(1)-0416 AIRFOIL | NASA/Langley/Somers NLF(1)-0416 natural laminar flow airfoil Max thickness 15.9% at 30.4% chord Max camber 2.5% at 34.8% chord | Remove Airfoil details Airfoil plotter |
(oaf095-il) OAF095 AIRFOIL | ONERA/Aerospatiale OAF095 Fenestron airfoil Max thickness 9.5% at 23.2% chord Max camber 3.9% at 53.1% chord | Remove Airfoil details Airfoil plotter |
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Polars for (fx601261-il,nlf416-il,oaf095-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx601261-il | 50,000 | 9 | 34.5 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx601261-il | 50,000 | 5 | 39.4 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx601261-il | 100,000 | 9 | 59.4 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx601261-il | 100,000 | 5 | 60.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx601261-il | 200,000 | 9 | 82.9 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx601261-il | 200,000 | 5 | 76.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx601261-il | 500,000 | 9 | 108.2 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx601261-il | 500,000 | 5 | 84.2 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx601261-il | 1,000,000 | 9 | 113.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx601261-il | 1,000,000 | 5 | 88.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlf416-il | 50,000 | 9 | 14.8 at α=0.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlf416-il | 50,000 | 5 | 25.7 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlf416-il | 100,000 | 9 | 45.1 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlf416-il | 100,000 | 5 | 48.3 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlf416-il | 200,000 | 9 | 65.3 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlf416-il | 200,000 | 5 | 67.3 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlf416-il | 500,000 | 9 | 93.7 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlf416-il | 500,000 | 5 | 91.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlf416-il | 1,000,000 | 9 | 115.7 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlf416-il | 1,000,000 | 5 | 108.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf095-il | 50,000 | 9 | 43.9 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf095-il | 50,000 | 5 | 43.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf095-il | 100,000 | 9 | 65.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf095-il | 100,000 | 5 | 63.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf095-il | 200,000 | 9 | 88.2 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf095-il | 200,000 | 5 | 82.8 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf095-il | 500,000 | 9 | 116.8 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf095-il | 500,000 | 5 | 93.2 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf095-il | 1,000,000 | 9 | 131.2 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf095-il | 1,000,000 | 5 | 98.3 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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