E212 (10.55%) (e212-il)
E212 (10.55%) - Eppler E212 low Reynolds number airfoil
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(e212-il) E212 (10.55%) Eppler E212 low Reynolds number airfoil Max thickness 10.6% at 27.5% chord. Max camber 2.5% at 61.3% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
E212 (10.55%) 1.00000 0.00000 0.99676 0.00092 0.98759 0.00372 0.97346 0.00803 0.95472 0.01307 0.93124 0.01844 0.90316 0.02418 0.87085 0.03023 0.83474 0.03645 0.79525 0.04269 0.75283 0.04881 0.70796 0.05465 0.66112 0.06008 0.61282 0.06496 0.56355 0.06915 0.51383 0.07256 0.46416 0.07507 0.41502 0.07660 0.36689 0.07708 0.32023 0.07647 0.27548 0.07473 0.23303 0.07188 0.19326 0.06794 0.15651 0.06295 0.12309 0.05701 0.09327 0.05023 0.06729 0.04275 0.04534 0.03473 0.02758 0.02636 0.01410 0.01790 0.00499 0.00967 0.00032 0.00224 0.00122 -0.00398 0.00800 -0.00970 0.01984 -0.01532 0.03648 -0.02045 0.05780 -0.02486 0.08363 -0.02840 0.11379 -0.03097 0.14808 -0.03252 0.18621 -0.03301 0.22790 -0.03248 0.27280 -0.03099 0.32051 -0.02861 0.37059 -0.02548 0.42257 -0.02175 0.47590 -0.01759 0.53003 -0.01320 0.58434 -0.00878 0.63819 -0.00452 0.69090 -0.00063 0.74179 0.00271 0.79016 0.00535 0.83528 0.00713 0.87643 0.00794 0.91284 0.00776 0.94382 0.00659 0.96851 0.00458 0.98615 0.00231 0.99657 0.00061 1.00000 0.00000 |
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Polars for E212 (10.55%) (e212-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e212-il | 50,000 | 9 | 38.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e212-il | 50,000 | 5 | 40.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e212-il | 100,000 | 9 | 59.9 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e212-il | 100,000 | 5 | 58.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e212-il | 200,000 | 9 | 81.7 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e212-il | 200,000 | 5 | 75.5 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e212-il | 500,000 | 9 | 108.4 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e212-il | 500,000 | 5 | 91.7 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e212-il | 1,000,000 | 9 | 119.8 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e212-il | 1,000,000 | 5 | 101 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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