AIRFOIL PROFILE12A 9.00% (rg12a-il)
AIRFOIL PROFILE12A 9.00% - Rolf Girsberger RG 12A airfoil
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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 Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
AIRFOIL PROFILE12A 9.00% 1.00000 0.0 0.99665 0.00059 0.98703 0.00246 0.97194 0.00551 0.95179 0.00921 0.92666 0.01325 0.89678 0.01766 0.86258 0.02238 0.82435 0.02731 0.78310 0.03232 0.73879 0.03730 0.69213 0.04212 0.64368 0.04674 0.59393 0.05104 0.54340 0.05487 0.49624 0.05790 0.44217 0.06058 0.39250 0.06222 0.34413 0.06294 0.29752 0.06267 0.25311 0.06138 0.21131 0.05906 0.17248 0.05573 0.13697 0.05143 0.10506 0.04625 0.07702 0.04030 0.05306 0.03373 0.03339 0.02671 0.01810 0.01942 0.00735 0.01226 0.00100 0.00531 0.0 0.0 0.00354 -0.00389 0.00953 -0.00703 0.02204 -0.01138 0.03760 -0.01484 0.05756 -0.01793 0.08143 -0.02053 0.10918 -0.02266 0.14059 -0.02434 0.17548 -0.02560 0.21358 -0.02646 0.25462 -0.02696 0.29829 -0.02711 0.34421 -0.02694 0.39199 -0.02647 0.44119 -0.02569 0.49132 -0.02461 0.54192 -0.02318 0.59248 -0.02135 0.64260 -0.01890 0.69148 -0.01559 0.73816 -0.01184 0.78233 -0.00827 0.82366 -0.00517 0.86166 -0.00266 0.89589 -0.00084 0.92587 0.00030 0.95113 0.00085 0.97147 0.00092 0.98682 0.00064 0.99661 0.00022 1.00000 0.0 |
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Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
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Polars for AIRFOIL PROFILE12A 9.00% (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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