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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(rg12a-il) AIRFOIL PROFILE12A 9.00% | Rolf Girsberger RG 12A airfoil Max thickness 9% at 34.4% chord Max camber 1.8% at 34.4% chord | Remove Airfoil details Airfoil plotter |
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Polars for (rg12a-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| rg12a-il | 50,000 | 9 | 34 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg12a-il | 50,000 | 5 | 35.9 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg12a-il | 100,000 | 9 | 50.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg12a-il | 100,000 | 5 | 49.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg12a-il | 200,000 | 9 | 67.1 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg12a-il | 200,000 | 5 | 62.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg12a-il | 500,000 | 9 | 86.7 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg12a-il | 500,000 | 5 | 75.3 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg12a-il | 1,000,000 | 9 | 96 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg12a-il | 1,000,000 | 5 | 83.5 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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