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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(fx73cl1152-il) FX 73-CL1-152 | Wortmann FX 73-CL1-152 airfoil Max thickness 15.2% at 22.2% chord Max camber 6.1% at 33.9% chord | Remove Airfoil details Airfoil plotter |
(fx082512-il) WORTMANN FX 082-512 AIRFOIL | Wortmann FX 082-512 airfoil Max thickness 11.8% at 25% chord Max camber 4.2% at 62.9% chord | Remove Airfoil details Airfoil plotter |
(fx67k150-il) FX 67-K-150/17 AIRFOIL | Wortmann FX 67-K-150/17 airfoil Max thickness 15% at 40.2% chord Max camber 4.8% at 43.5% chord | Remove Airfoil details Airfoil plotter |
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Polars for (fx73cl1152-il,fx082512-il,fx67k150-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx73cl1152-il | 50,000 | 9 | 4.9 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73cl1152-il | 50,000 | 5 | 20.7 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73cl1152-il | 100,000 | 9 | 24.5 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73cl1152-il | 100,000 | 5 | 42.1 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73cl1152-il | 200,000 | 9 | 53.3 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73cl1152-il | 200,000 | 5 | 68.7 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73cl1152-il | 500,000 | 9 | 100.8 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73cl1152-il | 500,000 | 5 | 106.5 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73cl1152-il | 1,000,000 | 9 | 137.4 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73cl1152-il | 1,000,000 | 5 | 136.8 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx082512-il | 50,000 | 9 | 31.2 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx082512-il | 50,000 | 5 | 33.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx082512-il | 100,000 | 9 | 46.6 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx082512-il | 100,000 | 5 | 47.7 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx082512-il | 200,000 | 9 | 63.6 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx082512-il | 200,000 | 5 | 60.2 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx082512-il | 500,000 | 9 | 83.7 at α=0.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx082512-il | 500,000 | 5 | 75.3 at α=-0.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx082512-il | 1,000,000 | 9 | 99.1 at α=-0.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx082512-il | 1,000,000 | 5 | 82.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx67k150-il | 50,000 | 9 | 5.8 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx67k150-il | 50,000 | 5 | 14.3 at α=12° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx67k150-il | 100,000 | 9 | 25 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx67k150-il | 100,000 | 5 | 27.1 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx67k150-il | 200,000 | 9 | 61.6 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx67k150-il | 200,000 | 5 | 68.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx67k150-il | 500,000 | 9 | 126.3 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx67k150-il | 500,000 | 5 | 118.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx67k150-il | 1,000,000 | 9 | 157.2 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx67k150-il | 1,000,000 | 5 | 147.8 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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