E475 (15.01%) (e475-il)
E475 (15.01%) - Eppler E475 aerobatic aircraft airfoil
| Details | Dat file | Parser | |
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(e475-il) E475 (15.01%) Eppler E475 aerobatic aircraft airfoil Max thickness 15% at 21.7% chord. Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
E475 (15.01%) 1.00000 0.00000 0.99608 0.00033 0.98478 0.00168 0.96708 0.00447 0.94380 0.00854 0.91560 0.01369 0.88326 0.01958 0.84723 0.02542 0.80734 0.03083 0.76375 0.03605 0.71704 0.04120 0.66781 0.04624 0.61667 0.05115 0.56426 0.05586 0.51124 0.06027 0.45826 0.06432 0.40598 0.06789 0.35504 0.07088 0.30609 0.07317 0.25973 0.07460 0.21656 0.07500 0.17717 0.07407 0.14181 0.07131 0.11033 0.06654 0.08267 0.05991 0.05881 0.05165 0.03879 0.04211 0.02270 0.03167 0.01065 0.02076 0.00283 0.00992 0.00000 0.00000 0.00283 -0.00992 0.01065 -0.02076 0.02270 -0.03167 0.03879 -0.04211 0.05881 -0.05165 0.08267 -0.05991 0.11033 -0.06654 0.14181 -0.07131 0.17717 -0.07407 0.21656 -0.07500 0.25973 -0.07460 0.30609 -0.07317 0.35504 -0.07088 0.40598 -0.06789 0.45826 -0.06432 0.51124 -0.06027 0.56426 -0.05586 0.61667 -0.05115 0.66781 -0.04624 0.71704 -0.04120 0.76375 -0.03605 0.80734 -0.03083 0.84723 -0.02542 0.88326 -0.01958 0.91560 -0.01369 0.94380 -0.00854 0.96708 -0.00447 0.98478 -0.00168 0.99608 -0.00033 1.00000 0.00000 |
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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 E475 (15.01%) (e475-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e475-il | 50,000 | 9 | 20.2 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e475-il | 50,000 | 5 | 24.1 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e475-il | 100,000 | 9 | 30.5 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e475-il | 100,000 | 5 | 36.3 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e475-il | 200,000 | 9 | 46.2 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e475-il | 200,000 | 5 | 51.3 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e475-il | 500,000 | 9 | 72.8 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e475-il | 500,000 | 5 | 71 at α=10.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e475-il | 1,000,000 | 9 | 90 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e475-il | 1,000,000 | 5 | 83.6 at α=10.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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