ESA40 (esa40-il)
ESA40 - Evans Simitar Airfoil ESA40 for R/C tailless aircraft
| Details | Dat file | Parser | |
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(esa40-il) ESA40 Evans Simitar Airfoil ESA40 for R/C tailless aircraft Max thickness 10.7% at 27.1% chord. Max camber 2% at 12% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
ESA40 1.000000 0.004450 0.997540 0.004521 0.990700 0.004603 0.980370 0.004515 0.966980 0.004211 0.950440 0.003748 0.930640 0.003167 0.907750 0.002388 0.882020 0.001578 0.853700 0.002132 0.823090 0.005572 0.790480 0.010199 0.756160 0.015054 0.720430 0.020294 0.683590 0.025638 0.645940 0.030800 0.607780 0.035771 0.569370 0.040633 0.530990 0.045353 0.492650 0.049829 0.454350 0.053959 0.416380 0.057687 0.378870 0.061045 0.342040 0.063997 0.306090 0.066434 0.271200 0.068276 0.237600 0.069523 0.205490 0.070194 0.175040 0.070224 0.146480 0.069444 0.119990 0.067601 0.095760 0.064436 0.073950 0.059758 0.054680 0.053529 0.038110 0.045990 0.024330 0.037596 0.013380 0.028281 0.005480 0.017182 0.000980 0.005977 0.000000 0.000022 0.000980 -0.003981 0.005480 -0.007533 0.013380 -0.010415 0.024330 -0.013550 0.038110 -0.016790 0.054680 -0.019718 0.073950 -0.022389 0.095760 -0.025007 0.119990 -0.027480 0.146480 -0.029696 0.175040 -0.031944 0.205490 -0.034411 0.237600 -0.036815 0.271200 -0.038899 0.306090 -0.040675 0.342040 -0.042243 0.378870 -0.043522 0.416380 -0.044296 0.454350 -0.044467 0.492650 -0.044085 0.530990 -0.043248 0.569370 -0.041963 0.607780 -0.040221 0.645940 -0.038161 0.683590 -0.036003 0.720430 -0.033900 0.756160 -0.031876 0.790480 -0.029811 0.823090 -0.027393 0.853700 -0.024131 0.882020 -0.020255 0.907750 -0.016698 0.930640 -0.013692 0.950440 -0.011083 0.966980 -0.008754 0.980370 -0.006790 0.990700 -0.005377 0.997540 -0.004624 0.999908 -0.004423 |
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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 ESA40 (esa40-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| esa40-il | 50,000 | 9 | 16 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| esa40-il | 50,000 | 5 | 21.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| esa40-il | 100,000 | 9 | 25.8 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| esa40-il | 100,000 | 5 | 32.7 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| esa40-il | 200,000 | 9 | 39.1 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| esa40-il | 200,000 | 5 | 47.3 at α=10.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| esa40-il | 500,000 | 9 | 66.3 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| esa40-il | 500,000 | 5 | 69.6 at α=10.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| esa40-il | 1,000,000 | 9 | 87.5 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| esa40-il | 1,000,000 | 5 | 86.4 at α=10.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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