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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(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 |
(fx057816-il) WORTMANN FX 057-816 | Wortmann FX 057-816 airfoil Max thickness 16.2% at 37.1% chord Max camber 5.1% at 37.1% chord | Remove Airfoil details Airfoil plotter |
(n64008a-il) NACA 64-008A AIRFOIL | NACA 64-008A airfoil Max thickness 8% at 40% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(fx05188-il) WORTMANN FX 05-188 AIRFOIL | Wortmann FX 05-188 airfoil Max thickness 18.8% at 37.1% chord Max camber 2.6% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (fx082512-il,fx057816-il,n64008a-il,fx05188-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| 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 | |
| fx057816-il | 50,000 | 9 | 5 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx057816-il | 50,000 | 5 | 11.1 at α=15.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx057816-il | 100,000 | 9 | 17.8 at α=13.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx057816-il | 100,000 | 5 | 16.5 at α=13.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx057816-il | 200,000 | 9 | 27.6 at α=12.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx057816-il | 200,000 | 5 | 27.1 at α=11.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx057816-il | 500,000 | 9 | 113.8 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx057816-il | 500,000 | 5 | 113.3 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx057816-il | 1,000,000 | 9 | 155.8 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx057816-il | 1,000,000 | 5 | 153 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n64008a-il | 50,000 | 9 | 19.1 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64008a-il | 50,000 | 5 | 23.3 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n64008a-il | 100,000 | 9 | 32.5 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64008a-il | 100,000 | 5 | 30.1 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n64008a-il | 200,000 | 9 | 41 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64008a-il | 200,000 | 5 | 35 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n64008a-il | 500,000 | 9 | 46.5 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64008a-il | 500,000 | 5 | 44.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n64008a-il | 1,000,000 | 9 | 49.9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64008a-il | 1,000,000 | 5 | 59.4 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx05188-il | 50,000 | 9 | 17.1 at α=14.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx05188-il | 50,000 | 5 | 14.2 at α=13° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx05188-il | 100,000 | 9 | 27.8 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx05188-il | 100,000 | 5 | 29.4 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx05188-il | 200,000 | 9 | 60.5 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx05188-il | 200,000 | 5 | 64.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx05188-il | 500,000 | 9 | 99.5 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx05188-il | 500,000 | 5 | 97.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx05188-il | 1,000,000 | 9 | 126.9 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx05188-il | 1,000,000 | 5 | 117.9 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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