EPPLER 396 AIRFOIL (e396-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 396 AIRFOIL (e396-il) Reynolds number: 1,000,000 Max Cl/Cd: 148 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e396-il-1000000-n5.txt Download as CSV file: xf-e396-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 396 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.4973 0.07945 0.07710 -0.0905 0.9861 0.0027
-13.500 -0.5329 0.06905 0.06659 -0.0980 0.9794 0.0026
-13.250 -0.5816 0.05645 0.05383 -0.1081 0.9622 0.0026
-12.750 -0.5933 0.02720 0.02375 -0.1551 0.9125 0.0025
-12.500 -0.5935 0.02379 0.02005 -0.1596 0.8830 0.0026
-12.250 -0.5862 0.02201 0.01805 -0.1601 0.8662 0.0025
-12.000 -0.5730 0.02071 0.01657 -0.1601 0.8544 0.0026
-11.500 -0.5364 0.01883 0.01442 -0.1601 0.8352 0.0028
-11.250 -0.5162 0.01798 0.01343 -0.1601 0.8270 0.0029
-11.000 -0.4948 0.01715 0.01248 -0.1601 0.8191 0.0030
-10.750 -0.4719 0.01650 0.01171 -0.1602 0.8124 0.0031
-10.500 -0.4485 0.01582 0.01092 -0.1602 0.8054 0.0032
-10.250 -0.4244 0.01522 0.01019 -0.1603 0.7992 0.0033
-10.000 -0.3995 0.01466 0.00952 -0.1604 0.7933 0.0034
-9.750 -0.3742 0.01418 0.00894 -0.1605 0.7874 0.0035
-9.500 -0.3483 0.01370 0.00837 -0.1606 0.7822 0.0035
-9.250 -0.3227 0.01312 0.00769 -0.1608 0.7765 0.0038
-8.750 -0.2696 0.01224 0.00666 -0.1611 0.7668 0.0044
-8.500 -0.2427 0.01187 0.00620 -0.1613 0.7617 0.0048
-8.000 -0.1880 0.01122 0.00542 -0.1617 0.7529 0.0058
-7.750 -0.1604 0.01088 0.00503 -0.1619 0.7482 0.0069
-7.500 -0.1329 0.01061 0.00470 -0.1620 0.7438 0.0082
-7.250 -0.1050 0.01030 0.00437 -0.1623 0.7398 0.0105
-7.000 -0.0770 0.01001 0.00406 -0.1626 0.7356 0.0138
-6.750 -0.0491 0.00975 0.00378 -0.1628 0.7312 0.0178
-6.500 -0.0211 0.00954 0.00354 -0.1630 0.7273 0.0218
-6.250 0.0074 0.00929 0.00331 -0.1633 0.7235 0.0271
-6.000 0.0357 0.00908 0.00309 -0.1635 0.7193 0.0326
-5.750 0.0640 0.00892 0.00290 -0.1637 0.7153 0.0377
-5.500 0.0924 0.00872 0.00271 -0.1640 0.7117 0.0462
-5.250 0.1211 0.00853 0.00255 -0.1643 0.7078 0.0553
-5.000 0.1496 0.00840 0.00240 -0.1645 0.7038 0.0624
-4.750 0.1780 0.00827 0.00226 -0.1647 0.7000 0.0715
-4.500 0.2068 0.00812 0.00213 -0.1650 0.6966 0.0827
-4.250 0.2356 0.00800 0.00202 -0.1653 0.6928 0.0924
-4.000 0.2642 0.00791 0.00192 -0.1655 0.6889 0.1018
-3.750 0.2926 0.00782 0.00182 -0.1657 0.6852 0.1139
-3.500 0.3215 0.00771 0.00174 -0.1660 0.6818 0.1257
-3.250 0.3503 0.00762 0.00167 -0.1663 0.6779 0.1397
-3.000 0.3789 0.00754 0.00161 -0.1665 0.6740 0.1549
-2.500 0.4362 0.00741 0.00151 -0.1669 0.6666 0.1820
-2.250 0.4650 0.00734 0.00148 -0.1672 0.6625 0.1981
-2.000 0.4934 0.00730 0.00145 -0.1674 0.6584 0.2122
-1.750 0.5219 0.00727 0.00143 -0.1675 0.6546 0.2279
-1.500 0.5507 0.00722 0.00141 -0.1678 0.6505 0.2413
-1.250 0.5792 0.00719 0.00140 -0.1680 0.6460 0.2570
-1.000 0.6073 0.00719 0.00141 -0.1681 0.6418 0.2721
-0.750 0.6360 0.00715 0.00141 -0.1683 0.6377 0.2881
-0.500 0.6645 0.00714 0.00142 -0.1685 0.6331 0.3034
-0.250 0.6925 0.00714 0.00144 -0.1686 0.6284 0.3202
0.000 0.7209 0.00712 0.00147 -0.1688 0.6240 0.3380
0.250 0.7493 0.00712 0.00150 -0.1690 0.6190 0.3558
0.500 0.7771 0.00714 0.00154 -0.1690 0.6139 0.3734
0.750 0.8053 0.00714 0.00158 -0.1692 0.6089 0.3923
1.000 0.8333 0.00715 0.00164 -0.1693 0.6031 0.4116
1.250 0.8608 0.00718 0.00169 -0.1693 0.5975 0.4321
1.500 0.8888 0.00720 0.00175 -0.1694 0.5913 0.4536
1.750 0.9161 0.00724 0.00183 -0.1694 0.5847 0.4756
2.250 0.9709 0.00732 0.00200 -0.1694 0.5707 0.5242
2.500 0.9981 0.00736 0.00210 -0.1693 0.5625 0.5489
2.750 1.0245 0.00745 0.00220 -0.1691 0.5531 0.5748
3.000 1.0511 0.00752 0.00232 -0.1690 0.5431 0.6022
3.250 1.0777 0.00760 0.00244 -0.1688 0.5339 0.6306
3.500 1.1036 0.00770 0.00259 -0.1686 0.5238 0.6602
3.750 1.1289 0.00782 0.00274 -0.1682 0.5116 0.6905
4.250 1.1795 0.00805 0.00308 -0.1674 0.4874 0.7598
4.500 1.2038 0.00817 0.00327 -0.1668 0.4754 0.7999
4.750 1.2264 0.00830 0.00347 -0.1658 0.4616 0.8477
5.000 1.2432 0.00840 0.00365 -0.1635 0.4455 0.9208
5.250 1.2642 0.00861 0.00385 -0.1622 0.4272 1.0000
5.500 1.2863 0.00893 0.00409 -0.1613 0.4088 1.0000
5.750 1.3081 0.00926 0.00434 -0.1603 0.3898 1.0000
6.000 1.3282 0.00966 0.00464 -0.1590 0.3681 1.0000
6.250 1.3459 0.01015 0.00499 -0.1573 0.3404 1.0000
6.500 1.3608 0.01070 0.00540 -0.1550 0.3108 1.0000
6.750 1.3748 0.01122 0.00580 -0.1526 0.2856 1.0000
7.000 1.3860 0.01184 0.00628 -0.1497 0.2570 1.0000
7.250 1.3982 0.01244 0.00676 -0.1471 0.2333 1.0000
7.500 1.4099 0.01307 0.00728 -0.1444 0.2107 1.0000
7.750 1.4193 0.01382 0.00789 -0.1414 0.1844 1.0000
8.000 1.4299 0.01454 0.00852 -0.1387 0.1633 1.0000
8.250 1.4396 0.01533 0.00920 -0.1360 0.1432 1.0000
8.500 1.4501 0.01609 0.00989 -0.1335 0.1273 1.0000
8.750 1.4601 0.01692 0.01065 -0.1310 0.1111 1.0000
9.000 1.4679 0.01791 0.01155 -0.1282 0.0933 1.0000
9.250 1.4778 0.01882 0.01242 -0.1259 0.0811 1.0000
9.500 1.4875 0.01978 0.01334 -0.1237 0.0701 1.0000
9.750 1.4966 0.02084 0.01436 -0.1215 0.0595 1.0000
10.000 1.5050 0.02197 0.01545 -0.1193 0.0496 1.0000
10.250 1.5126 0.02321 0.01665 -0.1172 0.0402 1.0000
10.500 1.5200 0.02451 0.01792 -0.1151 0.0320 1.0000
10.750 1.5282 0.02581 0.01921 -0.1133 0.0260 1.0000
11.000 1.5372 0.02709 0.02049 -0.1116 0.0214 1.0000
11.250 1.5451 0.02850 0.02190 -0.1099 0.0172 1.0000
11.500 1.5532 0.02993 0.02333 -0.1083 0.0142 1.0000
11.750 1.5622 0.03133 0.02476 -0.1069 0.0120 1.0000
12.000 1.5697 0.03289 0.02635 -0.1054 0.0097 1.0000
12.250 1.5788 0.03436 0.02786 -0.1041 0.0087 1.0000
12.500 1.5862 0.03602 0.02955 -0.1028 0.0070 1.0000
12.750 1.5939 0.03768 0.03125 -0.1016 0.0060 1.0000
13.000 1.6020 0.03936 0.03298 -0.1005 0.0053 1.0000
13.250 1.6092 0.04118 0.03484 -0.0995 0.0047 1.0000
13.500 1.6158 0.04308 0.03679 -0.0985 0.0041 1.0000
13.750 1.6230 0.04497 0.03874 -0.0976 0.0037 1.0000
14.000 1.6294 0.04699 0.04082 -0.0967 0.0032 1.0000
14.250 1.6352 0.04912 0.04301 -0.0959 0.0029 1.0000
14.500 1.6402 0.05140 0.04535 -0.0952 0.0025 1.0000
14.750 1.6458 0.05365 0.04767 -0.0946 0.0023 1.0000
15.000 1.6506 0.05604 0.05012 -0.0940 0.0021 1.0000
15.250 1.6550 0.05852 0.05267 -0.0936 0.0019 1.0000
15.500 1.6584 0.06119 0.05542 -0.0932 0.0017 1.0000
15.750 1.6611 0.06401 0.05831 -0.0929 0.0016 1.0000
16.000 1.6635 0.06691 0.06129 -0.0927 0.0014 1.0000
16.250 1.6663 0.06982 0.06428 -0.0926 0.0014 1.0000
16.500 1.6682 0.07292 0.06746 -0.0926 0.0013 1.0000
16.750 1.6697 0.07612 0.07075 -0.0927 0.0012 1.0000
17.000 1.6706 0.07946 0.07419 -0.0930 0.0012 1.0000
17.250 1.6710 0.08292 0.07773 -0.0933 0.0011 1.0000
17.500 1.6704 0.08660 0.08150 -0.0938 0.0011 1.0000
17.750 1.6691 0.09043 0.08543 -0.0944 0.0010 1.0000
18.000 1.6672 0.09442 0.08951 -0.0952 0.0010 1.0000
18.250 1.6649 0.09853 0.09372 -0.0961 0.0009 1.0000
18.500 1.6618 0.10282 0.09810 -0.0972 0.0009 1.0000
18.750 1.6582 0.10722 0.10261 -0.0984 0.0008 1.0000
19.000 1.6538 0.11183 0.10731 -0.0998 0.0008 1.0000
19.250 1.6489 0.11656 0.11215 -0.1014 0.0008 1.0000
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Polar data table (+)
Polar graphs
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