EPPLER 420 AIRFOIL (e420-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 420 AIRFOIL (e420-il) Reynolds number: 100,000 Max Cl/Cd: 47.77 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e420-il-100000-n5.txt Download as CSV file: xf-e420-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 0.3267 0.10427 0.09789 -0.1455 0.7527 0.0475
-9.750 0.3387 0.10208 0.09562 -0.1479 0.7421 0.0483
-9.500 0.3493 0.10012 0.09359 -0.1499 0.7320 0.0486
-9.000 0.3728 0.09553 0.08890 -0.1524 0.7138 0.0492
-8.750 0.3880 0.09306 0.08633 -0.1535 0.7060 0.0501
-8.500 0.3971 0.09123 0.08450 -0.1538 0.6975 0.0508
-8.250 0.4071 0.08932 0.08253 -0.1545 0.6899 0.0517
-8.000 0.4161 0.08750 0.08067 -0.1551 0.6832 0.0526
-7.750 0.4224 0.08589 0.07906 -0.1554 0.6761 0.0534
-7.500 0.4269 0.08435 0.07749 -0.1560 0.6699 0.0541
-7.250 0.4322 0.08277 0.07587 -0.1566 0.6647 0.0544
-7.000 0.4345 0.08129 0.07444 -0.1563 0.6585 0.0545
-6.750 0.4383 0.07971 0.07287 -0.1561 0.6532 0.0545
-6.500 0.4499 0.07742 0.07053 -0.1559 0.6485 0.0549
-6.250 0.4475 0.07640 0.06952 -0.1554 0.6440 0.0545
-6.000 0.4622 0.07413 0.06727 -0.1543 0.6386 0.0556
-5.750 0.4677 0.07275 0.06590 -0.1531 0.6337 0.0571
-5.500 0.4677 0.07168 0.06483 -0.1532 0.6294 0.0601
-5.000 0.4767 0.06649 0.05961 -0.1542 0.6214 0.0430
-4.500 0.4920 0.06174 0.05486 -0.1570 0.6132 0.0385
-4.250 0.5063 0.05976 0.05285 -0.1582 0.6097 0.0378
-4.000 0.5248 0.05717 0.05018 -0.1613 0.6068 0.0370
-3.750 0.5406 0.05457 0.04759 -0.1641 0.6031 0.0364
-3.500 0.5612 0.05145 0.04445 -0.1683 0.5993 0.0357
-3.250 0.5915 0.04747 0.04038 -0.1751 0.5956 0.0355
-3.000 0.6366 0.04225 0.03495 -0.1857 0.5922 0.0359
-2.750 0.7534 0.02762 0.01863 -0.2181 0.5893 0.0428
-2.500 0.7902 0.02647 0.01711 -0.2207 0.5864 0.0465
-2.250 0.8171 0.02592 0.01641 -0.2212 0.5826 0.0521
-2.000 0.8455 0.02543 0.01574 -0.2217 0.5791 0.0590
-1.750 0.8745 0.02511 0.01525 -0.2223 0.5758 0.0686
-1.500 0.9031 0.02504 0.01511 -0.2227 0.5729 0.0796
-1.250 0.9334 0.02491 0.01475 -0.2233 0.5702 0.0940
-1.000 0.9638 0.02495 0.01470 -0.2238 0.5678 0.1071
-0.750 0.9878 0.02509 0.01480 -0.2233 0.5646 0.1194
-0.500 1.0106 0.02525 0.01491 -0.2225 0.5612 0.1318
-0.250 1.0342 0.02547 0.01516 -0.2219 0.5580 0.1428
0.000 1.0597 0.02564 0.01527 -0.2216 0.5553 0.1543
0.250 1.0868 0.02576 0.01528 -0.2215 0.5529 0.1672
0.500 1.1151 0.02592 0.01531 -0.2217 0.5507 0.1807
0.750 1.1446 0.02606 0.01539 -0.2221 0.5487 0.1930
1.000 1.1667 0.02635 0.01564 -0.2212 0.5460 0.2049
1.250 1.1846 0.02675 0.01610 -0.2197 0.5427 0.2155
1.500 1.2050 0.02708 0.01644 -0.2185 0.5397 0.2267
1.750 1.2279 0.02741 0.01672 -0.2179 0.5372 0.2396
2.000 1.2526 0.02768 0.01700 -0.2175 0.5349 0.2513
2.250 1.2786 0.02793 0.01718 -0.2173 0.5328 0.2647
2.500 1.3066 0.02815 0.01729 -0.2174 0.5309 0.2794
2.750 1.3367 0.02833 0.01741 -0.2180 0.5290 0.2945
3.000 1.3463 0.02902 0.01824 -0.2151 0.5259 0.3053
3.250 1.3581 0.02969 0.01900 -0.2126 0.5228 0.3187
3.500 1.3733 0.03029 0.01967 -0.2108 0.5202 0.3334
3.750 1.3911 0.03081 0.02024 -0.2094 0.5178 0.3510
4.000 1.4126 0.03120 0.02068 -0.2086 0.5155 0.3740
4.250 1.4386 0.03145 0.02099 -0.2086 0.5135 0.4083
4.500 1.4692 0.03137 0.02126 -0.2094 0.5117 0.5566
4.750 1.4933 0.03126 0.02136 -0.2086 0.5101 1.0000
5.000 1.4741 0.03294 0.02325 -0.2015 0.5063 1.0000
5.250 1.4653 0.03452 0.02493 -0.1962 0.5028 1.0000
5.500 1.4682 0.03577 0.02621 -0.1929 0.4997 1.0000
5.750 1.4823 0.03659 0.02699 -0.1912 0.4972 1.0000
6.000 1.5051 0.03706 0.02740 -0.1907 0.4951 1.0000
6.250 1.5345 0.03730 0.02757 -0.1911 0.4935 1.0000
6.500 1.5672 0.03751 0.02768 -0.1920 0.4922 1.0000
6.750 1.4022 0.04905 0.03992 -0.1718 0.4785 1.0000
7.000 1.4279 0.04925 0.04008 -0.1716 0.4769 1.0000
7.250 1.4574 0.04920 0.03995 -0.1716 0.4757 1.0000
7.500 1.4894 0.04899 0.03968 -0.1720 0.4746 1.0000
7.750 1.5255 0.04852 0.03914 -0.1727 0.4738 1.0000
10.250 1.2467 0.11197 0.10373 -0.1571 0.3815 1.0000
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Polar data table (+)
Polar graphs
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