E230 (9.96%) (e230-il)
E230 (9.96%) - Eppler E230 airfoil
| Details | Dat file | Parser | |
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(e230-il) E230 (9.96%) Eppler E230 airfoil Max thickness 10% at 29.3% chord. Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
E230 (9.96%) 1.00000 0.00000 0.99657 -0.00018 0.98632 -0.00059 0.96935 -0.00078 0.94605 -0.00028 0.91713 0.00117 0.88330 0.00351 0.84515 0.00660 0.80327 0.01032 0.75825 0.01449 0.71067 0.01896 0.66113 0.02354 0.61019 0.02806 0.55840 0.03235 0.50634 0.03627 0.45455 0.03968 0.40355 0.04245 0.35387 0.04447 0.30597 0.04566 0.26032 0.04594 0.21733 0.04528 0.17740 0.04365 0.14085 0.04106 0.10801 0.03757 0.07914 0.03323 0.05449 0.02814 0.03424 0.02241 0.01853 0.01620 0.00744 0.00975 0.00107 0.00351 0.00045 -0.00235 0.00566 -0.00858 0.01567 -0.01534 0.03028 -0.02212 0.04937 -0.02861 0.07283 -0.03460 0.10048 -0.03994 0.13213 -0.04449 0.16753 -0.04819 0.20639 -0.05099 0.24838 -0.05286 0.29313 -0.05382 0.34021 -0.05392 0.38916 -0.05322 0.43946 -0.05178 0.49060 -0.04967 0.54202 -0.04698 0.59317 -0.04378 0.64349 -0.04018 0.69243 -0.03626 0.73944 -0.03213 0.78397 -0.02789 0.82552 -0.02364 0.86359 -0.01947 0.89769 -0.01549 0.92740 -0.01177 0.95228 -0.00830 0.97219 -0.00503 0.98712 -0.00225 0.99667 -0.00054 1.00000 0.00000 |
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Polars for E230 (9.96%) (e230-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e230-il | 50,000 | 9 | 23 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e230-il | 50,000 | 5 | 24.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e230-il | 100,000 | 9 | 32.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e230-il | 100,000 | 5 | 32.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e230-il | 200,000 | 9 | 41.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e230-il | 200,000 | 5 | 38.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e230-il | 500,000 | 9 | 50.4 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e230-il | 500,000 | 5 | 49.7 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e230-il | 1,000,000 | 9 | 57.7 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e230-il | 1,000,000 | 5 | 58 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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