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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(r1082-il) RONCZ 1082 VOYAGER ROOT OUTER AFT WING AIRFOIL | Roncz 1082 Voyager root outer aft wing airfoil Max thickness 18% at 40% chord Max camber 3.4% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (r1082-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| r1082-il | 50,000 | 9 | 4.2 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r1082-il | 50,000 | 5 | 12.1 at α=14.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r1082-il | 100,000 | 9 | 25.4 at α=13.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r1082-il | 100,000 | 5 | 21.5 at α=12.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r1082-il | 200,000 | 9 | 60.9 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r1082-il | 200,000 | 5 | 61.2 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r1082-il | 500,000 | 9 | 105.1 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r1082-il | 500,000 | 5 | 102.2 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r1082-il | 1,000,000 | 9 | 136.8 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r1082-il | 1,000,000 | 5 | 127.1 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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