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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(fx60100-il) FX 60-100 AIRFOIL | Wortmann FX 60-100 airfoil Max thickness 10% at 27.9% chord Max camber 3.6% at 56.5% chord | Remove Airfoil details Airfoil plotter |
(cast102-il) CAST 10-2/DOA 2 AIRFOIL | CAST 10-2/DOA 2 transonic airfoil Max thickness 12.2% at 45.4% chord Max camber 1.5% at 69.4% chord | Remove Airfoil details Airfoil plotter |
(goe12k-il) GOE 12K AIRFOIL | Gottingen 12K airfoil Max thickness 11.1% at 50% chord Max camber 4.1% at 60% chord | Remove Airfoil details Airfoil plotter |
(naca001066-il) NACA 0010-66 | NACA 0010-66 airfoil Max thickness 10% at 60% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (fx60100-il,cast102-il,goe12k-il,naca001066-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx60100-il | 50,000 | 9 | 40.5 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx60100-il | 50,000 | 5 | 42.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx60100-il | 100,000 | 9 | 62.7 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx60100-il | 100,000 | 5 | 61.4 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx60100-il | 200,000 | 9 | 84.9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx60100-il | 200,000 | 5 | 77.7 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx60100-il | 500,000 | 9 | 109.8 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx60100-il | 500,000 | 5 | 87.6 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx60100-il | 1,000,000 | 9 | 112.4 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx60100-il | 1,000,000 | 5 | 96.7 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cast102-il | 50,000 | 9 | 32.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cast102-il | 50,000 | 5 | 30.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cast102-il | 100,000 | 9 | 45.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cast102-il | 100,000 | 5 | 43 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cast102-il | 200,000 | 9 | 64 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cast102-il | 200,000 | 5 | 55.6 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cast102-il | 500,000 | 9 | 85.5 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cast102-il | 500,000 | 5 | 66.8 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cast102-il | 1,000,000 | 9 | 93.9 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cast102-il | 1,000,000 | 5 | 75.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe12k-il | 50,000 | 9 | 28.9 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe12k-il | 50,000 | 5 | 27.3 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe12k-il | 100,000 | 9 | 42.3 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe12k-il | 100,000 | 5 | 40.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe12k-il | 200,000 | 9 | 66.2 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe12k-il | 200,000 | 5 | 65.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe12k-il | 500,000 | 9 | 114 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe12k-il | 500,000 | 5 | 104.2 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe12k-il | 1,000,000 | 9 | 146.7 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe12k-il | 1,000,000 | 5 | 84.6 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca001066-il | 50,000 | 9 | 20.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca001066-il | 50,000 | 5 | 21.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca001066-il | 100,000 | 9 | 26.6 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca001066-il | 100,000 | 5 | 28.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca001066-il | 200,000 | 9 | 33.9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca001066-il | 200,000 | 5 | 34.4 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca001066-il | 500,000 | 9 | 42.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca001066-il | 500,000 | 5 | 47.1 at α=10.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca001066-il | 1,000,000 | 9 | 53.6 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca001066-il | 1,000,000 | 5 | 59.7 at α=10.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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