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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(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 (r1046-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| 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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