EPPLER 420 AIRFOIL (e420-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: EPPLER 420 AIRFOIL (e420-il) Reynolds number: 200,000 Max Cl/Cd: 63.27 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e420-il-200000.txt Download as CSV file: xf-e420-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 420 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 0.3845 0.09803 0.09329 -0.1659 0.7911 0.0386
-10.000 0.3892 0.09686 0.09200 -0.1678 0.7737 0.0388
-9.750 0.4071 0.09355 0.08856 -0.1676 0.7591 0.0392
-9.500 0.4194 0.09155 0.08642 -0.1682 0.7467 0.0397
-9.250 0.4280 0.08979 0.08462 -0.1681 0.7345 0.0405
-9.000 0.4381 0.08804 0.08277 -0.1687 0.7248 0.0411
-8.750 0.4450 0.08634 0.08104 -0.1688 0.7149 0.0423
-8.500 0.4519 0.08484 0.07944 -0.1699 0.7071 0.0432
-8.250 0.4478 0.08424 0.07888 -0.1708 0.6989 0.0436
-8.000 0.4643 0.08128 0.07585 -0.1701 0.6912 0.0440
-7.750 0.4772 0.07936 0.07385 -0.1702 0.6844 0.0445
-7.500 0.4854 0.07772 0.07224 -0.1697 0.6771 0.0456
-7.250 0.4935 0.07612 0.07059 -0.1697 0.6708 0.0467
-7.000 0.5001 0.07456 0.06896 -0.1706 0.6654 0.0482
-6.750 0.4907 0.07403 0.06853 -0.1708 0.6599 0.0487
-6.500 0.5064 0.07136 0.06584 -0.1700 0.6544 0.0493
-6.250 0.5182 0.06962 0.06406 -0.1696 0.6496 0.0499
-6.000 0.5287 0.06806 0.06244 -0.1696 0.6451 0.0511
-5.750 0.5306 0.06680 0.06125 -0.1683 0.6404 0.0524
-5.500 0.5251 0.06599 0.06049 -0.1692 0.6359 0.0543
-5.250 0.5322 0.06405 0.05855 -0.1707 0.6319 0.0548
-5.000 0.5485 0.06212 0.05655 -0.1693 0.6279 0.0557
-4.750 0.5603 0.06062 0.05505 -0.1695 0.6239 0.0571
-4.500 0.5696 0.05905 0.05353 -0.1704 0.6198 0.0591
-4.250 0.5851 0.05651 0.05100 -0.1770 0.6160 0.0612
-4.000 0.5980 0.05500 0.04947 -0.1749 0.6125 0.0624
-3.750 0.6170 0.05328 0.04770 -0.1765 0.6093 0.0646
-3.500 0.6528 0.04990 0.04418 -0.1868 0.6062 0.0685
-3.250 0.7356 0.03061 0.02430 -0.2196 0.6040 0.0433
-3.000 0.7963 0.02316 0.01555 -0.2327 0.6005 0.0430
-2.750 0.8282 0.02179 0.01384 -0.2342 0.5970 0.0446
-2.500 0.8591 0.02104 0.01283 -0.2350 0.5935 0.0478
-2.250 0.8903 0.02048 0.01208 -0.2358 0.5904 0.0529
-2.000 0.9224 0.02029 0.01174 -0.2367 0.5875 0.0624
-1.750 0.9500 0.02022 0.01162 -0.2368 0.5847 0.0751
-1.500 0.9753 0.02021 0.01172 -0.2364 0.5816 0.0887
-1.250 1.0018 0.02035 0.01180 -0.2362 0.5786 0.1045
-1.000 1.0290 0.02043 0.01188 -0.2361 0.5757 0.1190
-0.750 1.0571 0.02056 0.01196 -0.2362 0.5730 0.1329
-0.500 1.0864 0.02074 0.01206 -0.2364 0.5704 0.1465
-0.250 1.1170 0.02095 0.01223 -0.2371 0.5679 0.1600
0.000 1.1418 0.02112 0.01243 -0.2366 0.5654 0.1717
0.250 1.1654 0.02129 0.01258 -0.2359 0.5628 0.1844
0.500 1.1894 0.02150 0.01285 -0.2352 0.5601 0.1962
0.750 1.2149 0.02164 0.01299 -0.2349 0.5576 0.2084
1.000 1.2417 0.02185 0.01311 -0.2348 0.5550 0.2218
1.250 1.2696 0.02194 0.01321 -0.2349 0.5527 0.2347
1.500 1.2993 0.02208 0.01328 -0.2354 0.5505 0.2480
1.750 1.3300 0.02242 0.01351 -0.2361 0.5483 0.2624
2.000 1.3518 0.02273 0.01392 -0.2352 0.5462 0.2747
2.250 1.3725 0.02301 0.01430 -0.2341 0.5438 0.2867
2.500 1.3942 0.02333 0.01467 -0.2331 0.5413 0.3002
2.750 1.4169 0.02359 0.01499 -0.2324 0.5387 0.3143
3.000 1.4413 0.02379 0.01524 -0.2319 0.5363 0.3294
3.250 1.4680 0.02398 0.01545 -0.2319 0.5341 0.3472
3.500 1.4964 0.02420 0.01568 -0.2322 0.5322 0.3686
3.750 1.5262 0.02447 0.01599 -0.2329 0.5304 0.3962
4.000 1.5529 0.02492 0.01656 -0.2331 0.5284 0.4388
4.250 1.5627 0.02470 0.01719 -0.2299 0.5260 1.0000
4.500 1.5796 0.02526 0.01774 -0.2282 0.5233 1.0000
4.750 1.5981 0.02580 0.01828 -0.2268 0.5206 1.0000
5.000 1.6192 0.02630 0.01876 -0.2259 0.5183 1.0000
5.250 1.6424 0.02675 0.01919 -0.2253 0.5162 1.0000
5.500 1.6681 0.02712 0.01950 -0.2252 0.5142 1.0000
5.750 1.6978 0.02746 0.01977 -0.2258 0.5123 1.0000
6.000 1.7303 0.02801 0.02024 -0.2270 0.5104 1.0000
6.250 1.7342 0.02894 0.02132 -0.2232 0.5079 1.0000
6.500 1.7388 0.02988 0.02240 -0.2196 0.5050 1.0000
6.750 1.7496 0.03064 0.02323 -0.2171 0.5021 1.0000
7.000 1.7660 0.03121 0.02382 -0.2155 0.4994 1.0000
7.250 1.7883 0.03162 0.02423 -0.2149 0.4972 1.0000
7.500 1.8156 0.03191 0.02451 -0.2151 0.4952 1.0000
7.750 1.8490 0.03214 0.02468 -0.2164 0.4933 1.0000
8.000 1.8708 0.03290 0.02546 -0.2159 0.4910 1.0000
8.250 1.8309 0.03487 0.02770 -0.2051 0.4870 1.0000
8.500 1.8172 0.03636 0.02932 -0.1990 0.4834 1.0000
8.750 1.8274 0.03708 0.03010 -0.1966 0.4804 1.0000
9.000 1.8547 0.03721 0.03022 -0.1968 0.4783 1.0000
9.250 1.8942 0.03692 0.02989 -0.1988 0.4763 1.0000
9.500 1.9436 0.03660 0.02950 -0.2026 0.4745 1.0000
9.750 1.6999 0.05103 0.04461 -0.1709 0.4611 1.0000
10.000 1.7553 0.04870 0.04223 -0.1731 0.4607 1.0000
10.250 1.8121 0.04655 0.04003 -0.1758 0.4599 1.0000
10.500 1.8715 0.04446 0.03789 -0.1792 0.4589 1.0000
10.750 1.9316 0.04264 0.03600 -0.1830 0.4576 1.0000
11.000 2.0034 0.04084 0.03410 -0.1889 0.4560 1.0000
11.250 1.7436 0.06024 0.05408 -0.1627 0.4398 1.0000
11.500 1.8039 0.05672 0.05054 -0.1644 0.4399 1.0000
11.750 1.8691 0.05317 0.04695 -0.1668 0.4398 1.0000
12.000 1.9422 0.04947 0.04320 -0.1705 0.4393 1.0000
12.250 1.3858 0.12053 0.11494 -0.1576 0.3617 1.0000
12.500 1.4134 0.11951 0.11394 -0.1569 0.3609 1.0000
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Polar data table (+)
Polar graphs
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