EPPLER EC 86(-3)-914 AIRFOIL (ec863914-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER EC 86(-3)-914 AIRFOIL (ec863914-il) Reynolds number: 500,000 Max Cl/Cd: 98.12 at α=0.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ec863914-il-500000-n5.txt Download as CSV file: xf-ec863914-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER EC 86(-3)-914 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.000 -0.2102 0.15120 0.14841 -0.1062 0.9749 0.0085
-15.750 -0.2001 0.14859 0.14579 -0.1081 0.9746 0.0088
-15.500 -0.1903 0.14559 0.14280 -0.1101 0.9743 0.0092
-15.250 -0.1835 0.14114 0.13835 -0.1126 0.9740 0.0090
-8.500 -0.3234 0.02575 0.02055 -0.1475 0.9135 0.0074
-8.250 -0.3017 0.02396 0.01853 -0.1474 0.9126 0.0067
-8.000 -0.2758 0.02270 0.01703 -0.1480 0.9119 0.0062
-7.750 -0.2479 0.02174 0.01594 -0.1488 0.9114 0.0061
-7.500 -0.2558 0.02168 0.01583 -0.1426 0.9047 0.0060
-7.250 -0.2311 0.02089 0.01496 -0.1427 0.9032 0.0060
-7.000 -0.2049 0.01982 0.01387 -0.1433 0.9022 0.0061
-6.750 -0.1756 0.01873 0.01277 -0.1446 0.9014 0.0064
-6.500 -0.1432 0.01779 0.01180 -0.1466 0.9008 0.0069
-6.250 -0.1088 0.01699 0.01094 -0.1487 0.9004 0.0069
-6.000 -0.0735 0.01627 0.01017 -0.1509 0.9000 0.0068
-5.750 -0.0377 0.01564 0.00948 -0.1531 0.8997 0.0066
-5.500 -0.0276 0.01555 0.00936 -0.1501 0.8941 0.0065
-5.250 0.0034 0.01512 0.00889 -0.1513 0.8925 0.0064
-5.000 0.0370 0.01470 0.00843 -0.1528 0.8916 0.0062
-4.750 0.0714 0.01431 0.00798 -0.1545 0.8909 0.0061
-4.500 0.1063 0.01393 0.00757 -0.1563 0.8902 0.0061
-4.250 0.1414 0.01360 0.00719 -0.1580 0.8897 0.0060
-4.000 0.1771 0.01327 0.00682 -0.1598 0.8893 0.0060
-3.750 0.2132 0.01297 0.00648 -0.1616 0.8888 0.0059
-3.500 0.2496 0.01268 0.00616 -0.1636 0.8884 0.0059
-3.250 0.2866 0.01241 0.00586 -0.1656 0.8880 0.0060
-3.000 0.2972 0.01253 0.00596 -0.1623 0.8812 0.0060
-2.750 0.3321 0.01224 0.00566 -0.1638 0.8798 0.0061
-2.500 0.3692 0.01191 0.00530 -0.1657 0.8785 0.0066
-2.250 0.4078 0.01158 0.00497 -0.1679 0.8774 0.0070
-2.000 0.4606 0.01058 0.00447 -0.1739 0.8767 0.1697
-1.750 0.4818 0.01029 0.00441 -0.1730 0.8692 0.2248
-1.500 0.5336 0.00938 0.00400 -0.1788 0.8660 0.3544
-1.250 0.5725 0.00890 0.00382 -0.1816 0.8615 0.4465
-1.000 0.6035 0.00858 0.00369 -0.1826 0.8537 0.5060
-0.750 0.6297 0.00843 0.00376 -0.1822 0.8428 0.5752
-0.500 0.6560 0.00838 0.00377 -0.1818 0.8320 0.6068
-0.250 0.6873 0.00827 0.00365 -0.1824 0.8196 0.6232
0.000 0.7241 0.00811 0.00343 -0.1840 0.8031 0.6351
0.250 0.7685 0.00796 0.00315 -0.1872 0.7750 0.6445
0.750 0.8252 0.00841 0.00315 -0.1873 0.7020 0.6562
1.000 0.8407 0.00881 0.00336 -0.1846 0.6653 0.6605
1.250 0.8533 0.00926 0.00361 -0.1815 0.6246 0.6652
1.500 0.8669 0.00976 0.00390 -0.1787 0.5858 0.6703
1.750 0.8807 0.01028 0.00426 -0.1759 0.5474 0.6756
2.000 0.8972 0.01079 0.00459 -0.1738 0.5131 0.6815
2.250 0.9149 0.01126 0.00492 -0.1719 0.4808 0.6861
2.500 0.9332 0.01173 0.00527 -0.1701 0.4505 0.6903
2.750 0.9527 0.01219 0.00560 -0.1686 0.4218 0.6950
3.000 0.9731 0.01264 0.00591 -0.1674 0.3941 0.6992
3.250 0.9927 0.01309 0.00626 -0.1659 0.3674 0.7024
3.500 1.0131 0.01353 0.00661 -0.1646 0.3434 0.7057
3.750 1.0349 0.01393 0.00693 -0.1637 0.3232 0.7086
4.000 1.0574 0.01430 0.00723 -0.1629 0.3062 0.7106
4.250 1.0803 0.01467 0.00753 -0.1622 0.2908 0.7119
4.500 1.1033 0.01502 0.00783 -0.1615 0.2770 0.7130
4.750 1.1259 0.01537 0.00815 -0.1608 0.2645 0.7139
5.000 1.1484 0.01572 0.00849 -0.1600 0.2535 0.7150
5.250 1.1705 0.01610 0.00884 -0.1591 0.2426 0.7161
5.500 1.1929 0.01646 0.00921 -0.1584 0.2325 0.7172
5.750 1.2151 0.01683 0.00958 -0.1576 0.2242 0.7183
6.000 1.2368 0.01725 0.00998 -0.1567 0.2155 0.7193
6.250 1.2585 0.01766 0.01038 -0.1558 0.2051 0.7205
6.500 1.2798 0.01810 0.01081 -0.1549 0.1951 0.7216
6.750 1.3005 0.01860 0.01127 -0.1540 0.1831 0.7228
7.000 1.3210 0.01913 0.01175 -0.1530 0.1706 0.7240
7.250 1.3423 0.01958 0.01220 -0.1521 0.1612 0.7255
7.500 1.3627 0.02010 0.01270 -0.1511 0.1499 0.7269
7.750 1.3805 0.02084 0.01331 -0.1498 0.1286 0.7281
8.000 1.3822 0.02299 0.01487 -0.1462 0.0477 0.7290
8.250 1.3865 0.02498 0.01660 -0.1430 0.0058 0.7298
8.500 1.4034 0.02579 0.01748 -0.1415 0.0043 0.7309
8.750 1.4206 0.02658 0.01836 -0.1400 0.0037 0.7319
9.000 1.4377 0.02737 0.01924 -0.1387 0.0034 0.7330
9.250 1.4540 0.02823 0.02019 -0.1372 0.0032 0.7342
9.500 1.4695 0.02917 0.02124 -0.1356 0.0029 0.7354
9.750 1.4838 0.03020 0.02237 -0.1340 0.0027 0.7367
10.000 1.4974 0.03132 0.02359 -0.1323 0.0025 0.7380
10.250 1.5092 0.03257 0.02497 -0.1304 0.0024 0.7393
10.500 1.5191 0.03402 0.02654 -0.1284 0.0023 0.7406
10.750 1.5257 0.03577 0.02841 -0.1260 0.0021 0.7420
11.000 1.5282 0.03790 0.03069 -0.1233 0.0020 0.7433
11.250 1.5384 0.03930 0.03220 -0.1216 0.0019 0.7445
11.500 1.5466 0.04091 0.03392 -0.1198 0.0018 0.7457
11.750 1.5536 0.04267 0.03579 -0.1180 0.0017 0.7469
12.000 1.5613 0.04440 0.03764 -0.1164 0.0016 0.7482
12.250 1.5645 0.04664 0.04001 -0.1145 0.0015 0.7494
12.500 1.5654 0.04919 0.04269 -0.1127 0.0015 0.7507
12.750 1.5672 0.05177 0.04540 -0.1112 0.0014 0.7520
13.000 1.5675 0.05461 0.04837 -0.1098 0.0014 0.7534
13.250 1.5648 0.05792 0.05183 -0.1085 0.0013 0.7547
13.500 1.5636 0.06119 0.05523 -0.1076 0.0013 0.7560
13.750 1.5598 0.06496 0.05913 -0.1070 0.0012 0.7573
14.000 1.5559 0.06893 0.06327 -0.1067 0.0012 0.7585
14.250 1.5497 0.07337 0.06786 -0.1068 0.0012 0.7596
14.500 1.5423 0.07823 0.07288 -0.1072 0.0012 0.7606
14.750 1.5337 0.08347 0.07828 -0.1081 0.0011 0.7617
15.000 1.5258 0.08881 0.08377 -0.1094 0.0011 0.7627
15.250 1.5146 0.09494 0.09006 -0.1112 0.0011 0.7638
15.500 1.5045 0.10108 0.09636 -0.1133 0.0011 0.7649
15.750 1.4930 0.10764 0.10308 -0.1158 0.0011 0.7660
16.000 1.4820 0.11423 0.10981 -0.1186 0.0010 0.7671
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