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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(naca633218-il) NACA 63(3)-218 | NACA 63(3)-218 airfoil Max thickness 18% at 34.9% chord Max camber 1.1% at 24.9% chord | Remove Airfoil details Airfoil plotter |
(ag47ct02r-il) AG47ct -02f rot. | Drela AG47ct -02f airfoil Max thickness 5% at 22.5% chord Max camber 1.2% at 33.4% chord | Remove Airfoil details Airfoil plotter |
(fx63137sm-il) FX 63-137 13.7% smoothed | Wortmann FX 63-137 airfoil (smoothed) Max thickness 13.7% at 30.9% chord Max camber 5.8% at 56.5% chord | Remove Airfoil details Airfoil plotter |
(nlr1t-il) NLR-1T AIRFOIL | Bell/NASA/NLR NLR-1T rotorcraft airfoil Max thickness 8.7% at 38.3% chord Max camber 1.3% at 22.3% chord | Remove Airfoil details Airfoil plotter |
(naca63209-il) NACA 63-209 | NACA 63-209 airfoil Max thickness 9% at 35% chord Max camber 1.1% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (naca633218-il,ag47ct02r-il,fx63137sm-il,nlr1t-il,naca63209-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca633218-il | 50,000 | 9 | 22.2 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca633218-il | 50,000 | 5 | 21.8 at α=10.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca633218-il | 100,000 | 9 | 43 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca633218-il | 100,000 | 5 | 38.8 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca633218-il | 200,000 | 9 | 51.9 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca633218-il | 200,000 | 5 | 49.6 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca633218-il | 500,000 | 9 | 67.8 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca633218-il | 500,000 | 5 | 63.9 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca633218-il | 1,000,000 | 9 | 81.6 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca633218-il | 1,000,000 | 5 | 75.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag47ct02r-il | 50,000 | 9 | 30.5 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag47ct02r-il | 50,000 | 5 | 30.3 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag47ct02r-il | 100,000 | 9 | 41.9 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag47ct02r-il | 100,000 | 5 | 38.9 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag47ct02r-il | 200,000 | 9 | 52.1 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag47ct02r-il | 200,000 | 5 | 49.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag47ct02r-il | 500,000 | 9 | 65.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag47ct02r-il | 500,000 | 5 | 66.7 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag47ct02r-il | 1,000,000 | 9 | 80.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag47ct02r-il | 1,000,000 | 5 | 80.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63137sm-il | 50,000 | 9 | 25.9 at α=11.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63137sm-il | 50,000 | 5 | 31.6 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63137sm-il | 100,000 | 9 | 60.5 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63137sm-il | 100,000 | 5 | 64.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63137sm-il | 200,000 | 9 | 91.5 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63137sm-il | 200,000 | 5 | 88.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63137sm-il | 500,000 | 9 | 125.6 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63137sm-il | 500,000 | 5 | 117.9 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63137sm-il | 1,000,000 | 9 | 151.5 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63137sm-il | 1,000,000 | 5 | 137.6 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlr1t-il | 50,000 | 9 | 29.6 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlr1t-il | 50,000 | 5 | 28.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlr1t-il | 100,000 | 9 | 38.9 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlr1t-il | 100,000 | 5 | 39.5 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlr1t-il | 200,000 | 9 | 53.4 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlr1t-il | 200,000 | 5 | 52 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlr1t-il | 500,000 | 9 | 70.5 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlr1t-il | 500,000 | 5 | 68.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlr1t-il | 1,000,000 | 9 | 84.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlr1t-il | 1,000,000 | 5 | 80.9 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca63209-il | 50,000 | 9 | 32.1 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca63209-il | 50,000 | 5 | 32.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca63209-il | 100,000 | 9 | 47.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca63209-il | 100,000 | 5 | 44.5 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca63209-il | 200,000 | 9 | 62 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca63209-il | 200,000 | 5 | 55.5 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca63209-il | 500,000 | 9 | 78 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca63209-il | 500,000 | 5 | 63.4 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca63209-il | 1,000,000 | 9 | 84.6 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca63209-il | 1,000,000 | 5 | 72.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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