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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(fx711525-il) FX 71-L-150/25 AIRFOIL | Wortmann FX 71-L-150/25 airfoil Max thickness 15% at 33.9% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(r1046-il) RONCZ 1046 VOYAGER CANARD AIRFOIL | Roncz 1046 Voyager canard airfoil Max thickness 18.1% at 38% chord Max camber 6.7% at 42% chord | Remove Airfoil details Airfoil plotter |
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Polars for (fx711525-il,r1046-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx711525-il | 50,000 | 9 | 27.4 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx711525-il | 50,000 | 5 | 26.8 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx711525-il | 100,000 | 9 | 38.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx711525-il | 100,000 | 5 | 34.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx711525-il | 200,000 | 9 | 46.1 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx711525-il | 200,000 | 5 | 39.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx711525-il | 500,000 | 9 | 50.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx711525-il | 500,000 | 5 | 48.3 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx711525-il | 1,000,000 | 9 | 58.2 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx711525-il | 1,000,000 | 5 | 57.4 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r1046-il | 50,000 | 9 | 4.4 at α=12.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r1046-il | 50,000 | 5 | 6.9 at α=12.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r1046-il | 100,000 | 9 | 13 at α=19° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r1046-il | 100,000 | 5 | 20.5 at α=1° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r1046-il | 200,000 | 9 | 26.5 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r1046-il | 200,000 | 5 | 54.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r1046-il | 500,000 | 9 | 101.4 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r1046-il | 500,000 | 5 | 108.1 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r1046-il | 1,000,000 | 9 | 148.8 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r1046-il | 1,000,000 | 5 | 149.6 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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