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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(rg8-il) RG 8 AIRFOIL | Rolf Girsberger RG 8 airfoil Max thickness 10.8% at 31.1% chord Max camber 2.2% at 60.5% chord | Remove Airfoil details Airfoil plotter |
(rg12a189-il) RG 12A-1.8/9.0 AIRFOIL | Rolf Girsberger RG 12A-1.8/9.0 airfoil Max thickness 9% at 34.4% chord Max camber 1.8% at 34.4% chord | Remove Airfoil details Airfoil plotter |
(rc1064c-il) NASA/LANGLEY RC10-64C AIRFOIL | NASA/Langley 10-64C rotorcraft airfoil Max thickness 10% at 40% chord Max camber 1% at 35% chord | Remove Airfoil details Airfoil plotter |
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Polars for (rg8-il,rg12a189-il,rc1064c-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| rg8-il | 50,000 | 9 | 35.5 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg8-il | 50,000 | 5 | 37.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg8-il | 100,000 | 9 | 54.8 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg8-il | 100,000 | 5 | 53.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg8-il | 200,000 | 9 | 73.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg8-il | 200,000 | 5 | 68.3 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg8-il | 500,000 | 9 | 96.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg8-il | 500,000 | 5 | 83.3 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg8-il | 1,000,000 | 9 | 107.5 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg8-il | 1,000,000 | 5 | 92.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg12a189-il | 50,000 | 9 | 34 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg12a189-il | 50,000 | 5 | 35.9 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg12a189-il | 100,000 | 9 | 50.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg12a189-il | 100,000 | 5 | 49.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg12a189-il | 200,000 | 9 | 67.1 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg12a189-il | 200,000 | 5 | 62.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg12a189-il | 500,000 | 9 | 86.7 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg12a189-il | 500,000 | 5 | 74.7 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg12a189-il | 1,000,000 | 9 | 96.2 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg12a189-il | 1,000,000 | 5 | 83.5 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc1064c-il | 50,000 | 9 | 31.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc1064c-il | 50,000 | 5 | 30.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc1064c-il | 100,000 | 9 | 45.4 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc1064c-il | 100,000 | 5 | 41.9 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc1064c-il | 200,000 | 9 | 57.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc1064c-il | 200,000 | 5 | 46.6 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc1064c-il | 500,000 | 9 | 62.4 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc1064c-il | 500,000 | 5 | 59.4 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc1064c-il | 1,000,000 | 9 | 71.2 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc1064c-il | 1,000,000 | 5 | 73.2 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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