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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(r140-il) R140 (original) | R140 Quickee 500 airfoil (original) Max thickness 12% at 39.3% chord Max camber 0.5% at 42.3% chord | Remove Airfoil details Airfoil plotter |
(r1082t-il) RONCZ 1082T VOYAGER TIP OUTER AFT WING AIRFOIL | Roncz 1082T Voyager tip outer aft wing airfoil Max thickness 16% at 40% chord Max camber 3% at 40% chord | Remove Airfoil details Airfoil plotter |
(rae100-il) RAE 100 AIRFOIL | RAE 100 airfoil Max thickness 10% at 26% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(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 (r140-il,r1082t-il,rae100-il,r1082-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| r140-il | 50,000 | 9 | 27.1 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r140-il | 50,000 | 5 | 28.7 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r140-il | 100,000 | 9 | 43.2 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r140-il | 100,000 | 5 | 36.1 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r140-il | 200,000 | 9 | 48.6 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r140-il | 200,000 | 5 | 33.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r140-il | 500,000 | 9 | 47.1 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r140-il | 500,000 | 5 | 37.5 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r140-il | 1,000,000 | 9 | 50.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r140-il | 1,000,000 | 5 | 71.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r1082t-il | 50,000 | 9 | 21.7 at α=12.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r1082t-il | 50,000 | 5 | 16.5 at α=12.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r1082t-il | 100,000 | 9 | 34.3 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r1082t-il | 100,000 | 5 | 38.2 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r1082t-il | 200,000 | 9 | 73.2 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r1082t-il | 200,000 | 5 | 69.4 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r1082t-il | 500,000 | 9 | 107.6 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r1082t-il | 500,000 | 5 | 101.6 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r1082t-il | 1,000,000 | 9 | 135 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r1082t-il | 1,000,000 | 5 | 122.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae100-il | 50,000 | 9 | 24.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae100-il | 50,000 | 5 | 26.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae100-il | 100,000 | 9 | 35.3 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae100-il | 100,000 | 5 | 35.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae100-il | 200,000 | 9 | 46.1 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae100-il | 200,000 | 5 | 45 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae100-il | 500,000 | 9 | 60.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae100-il | 500,000 | 5 | 60.9 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae100-il | 1,000,000 | 9 | 74.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae100-il | 1,000,000 | 5 | 74.8 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| 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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