EPPLER 397 AIRFOIL (e397-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 397 AIRFOIL (e397-il) Reynolds number: 1,000,000 Max Cl/Cd: 139.9 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e397-il-1000000-n5.txt Download as CSV file: xf-e397-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 397 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
------ -------- --------- --------- -------- -------- --------
-14.500 -0.5310 0.08377 0.08131 -0.0895 0.9890 0.0025
-14.250 -0.5527 0.07515 0.07258 -0.0959 0.9852 0.0022
-14.000 -0.5943 0.06462 0.06191 -0.1029 0.9765 0.0022
-13.750 -0.6261 0.05467 0.05180 -0.1113 0.9616 0.0022
-13.500 -0.6299 0.04516 0.04209 -0.1244 0.9485 0.0021
-13.250 -0.6182 0.03185 0.02836 -0.1491 0.9303 0.0022
-13.000 -0.6037 0.02693 0.02313 -0.1581 0.8990 0.0022
-12.500 -0.6189 0.02168 0.01740 -0.1597 0.8531 0.0023
-12.250 -0.6073 0.02047 0.01605 -0.1595 0.8419 0.0023
-12.000 -0.5920 0.01946 0.01490 -0.1592 0.8327 0.0024
-11.500 -0.5545 0.01780 0.01299 -0.1589 0.8162 0.0026
-11.250 -0.5338 0.01709 0.01216 -0.1588 0.8088 0.0026
-11.000 -0.5115 0.01642 0.01140 -0.1588 0.8028 0.0028
-10.750 -0.4885 0.01582 0.01069 -0.1587 0.7966 0.0029
-10.500 -0.4647 0.01526 0.01003 -0.1587 0.7910 0.0031
-10.250 -0.4402 0.01472 0.00940 -0.1588 0.7852 0.0032
-10.000 -0.4154 0.01427 0.00885 -0.1588 0.7794 0.0033
-9.750 -0.3903 0.01372 0.00821 -0.1589 0.7746 0.0036
-9.500 -0.3646 0.01324 0.00766 -0.1591 0.7698 0.0039
-9.250 -0.3386 0.01283 0.00718 -0.1592 0.7649 0.0043
-9.000 -0.3122 0.01246 0.00672 -0.1593 0.7605 0.0047
-8.750 -0.2853 0.01210 0.00631 -0.1595 0.7558 0.0051
-8.500 -0.2585 0.01173 0.00588 -0.1597 0.7512 0.0059
-8.000 -0.2039 0.01109 0.00514 -0.1601 0.7435 0.0082
-7.750 -0.1763 0.01079 0.00481 -0.1603 0.7393 0.0101
-7.500 -0.1487 0.01052 0.00450 -0.1605 0.7351 0.0124
-7.250 -0.1211 0.01027 0.00421 -0.1607 0.7314 0.0151
-7.000 -0.0929 0.01000 0.00393 -0.1611 0.7280 0.0185
-6.750 -0.0648 0.00974 0.00367 -0.1613 0.7243 0.0237
-6.500 -0.0368 0.00951 0.00343 -0.1616 0.7205 0.0292
-6.000 0.0197 0.00906 0.00300 -0.1622 0.7137 0.0451
-5.750 0.0482 0.00884 0.00281 -0.1625 0.7103 0.0551
-5.500 0.0767 0.00866 0.00264 -0.1628 0.7067 0.0641
-5.250 0.1051 0.00851 0.00248 -0.1630 0.7032 0.0726
-5.000 0.1337 0.00835 0.00233 -0.1633 0.7002 0.0831
-4.750 0.1625 0.00821 0.00221 -0.1636 0.6972 0.0936
-4.500 0.1913 0.00809 0.00209 -0.1639 0.6938 0.1041
-4.250 0.2199 0.00797 0.00198 -0.1642 0.6904 0.1156
-4.000 0.2484 0.00787 0.00189 -0.1645 0.6872 0.1282
-3.750 0.2773 0.00776 0.00180 -0.1648 0.6844 0.1415
-3.500 0.3062 0.00765 0.00173 -0.1651 0.6812 0.1554
-3.250 0.3351 0.00757 0.00166 -0.1654 0.6779 0.1688
-3.000 0.3637 0.00751 0.00161 -0.1656 0.6748 0.1813
-2.750 0.3922 0.00745 0.00156 -0.1658 0.6716 0.1959
-2.500 0.4212 0.00738 0.00152 -0.1661 0.6688 0.2110
-2.250 0.4501 0.00732 0.00149 -0.1664 0.6657 0.2243
-1.750 0.5074 0.00724 0.00145 -0.1669 0.6591 0.2531
-1.500 0.5358 0.00722 0.00144 -0.1671 0.6560 0.2678
-1.250 0.5647 0.00718 0.00144 -0.1674 0.6531 0.2809
-1.000 0.5935 0.00714 0.00144 -0.1676 0.6497 0.2955
-0.750 0.6221 0.00712 0.00145 -0.1679 0.6463 0.3093
-0.500 0.6504 0.00712 0.00146 -0.1680 0.6428 0.3238
-0.250 0.6788 0.00712 0.00148 -0.1682 0.6396 0.3376
0.000 0.7075 0.00710 0.00151 -0.1685 0.6361 0.3527
0.250 0.7359 0.00709 0.00154 -0.1686 0.6322 0.3674
0.500 0.7640 0.00711 0.00157 -0.1688 0.6282 0.3828
0.750 0.7921 0.00712 0.00161 -0.1689 0.6243 0.3985
1.000 0.8205 0.00711 0.00166 -0.1691 0.6197 0.4151
1.250 0.8484 0.00713 0.00171 -0.1692 0.6147 0.4321
1.500 0.8760 0.00716 0.00177 -0.1692 0.6100 0.4502
1.750 0.9042 0.00717 0.00184 -0.1694 0.6046 0.4696
2.000 0.9315 0.00721 0.00190 -0.1693 0.5982 0.4889
2.250 0.9591 0.00724 0.00198 -0.1694 0.5920 0.5087
2.500 0.9861 0.00729 0.00207 -0.1693 0.5838 0.5291
2.750 1.0130 0.00734 0.00216 -0.1692 0.5749 0.5507
3.000 1.0387 0.00745 0.00227 -0.1689 0.5613 0.5724
3.250 1.0632 0.00760 0.00240 -0.1683 0.5417 0.5945
3.500 1.0864 0.00782 0.00257 -0.1675 0.5185 0.6178
3.750 1.1101 0.00802 0.00275 -0.1668 0.4978 0.6413
4.250 1.1552 0.00854 0.00320 -0.1650 0.4522 0.6921
4.500 1.1763 0.00886 0.00347 -0.1639 0.4271 0.7198
4.750 1.1953 0.00927 0.00380 -0.1624 0.3951 0.7478
5.000 1.2138 0.00966 0.00414 -0.1608 0.3662 0.7814
5.250 1.2320 0.01002 0.00448 -0.1590 0.3415 0.8192
5.500 1.2478 0.01035 0.00482 -0.1568 0.3172 0.8700
5.750 1.2569 0.01058 0.00510 -0.1531 0.2954 1.0000
6.000 1.2722 0.01102 0.00545 -0.1509 0.2730 1.0000
6.250 1.2853 0.01156 0.00586 -0.1483 0.2491 1.0000
6.500 1.2982 0.01212 0.00630 -0.1457 0.2246 1.0000
6.750 1.3108 0.01270 0.00678 -0.1432 0.2025 1.0000
7.000 1.3233 0.01329 0.00727 -0.1407 0.1818 1.0000
7.250 1.3354 0.01392 0.00781 -0.1382 0.1633 1.0000
7.500 1.3479 0.01455 0.00837 -0.1359 0.1464 1.0000
7.750 1.3551 0.01545 0.00913 -0.1328 0.1216 1.0000
8.000 1.3658 0.01622 0.00983 -0.1303 0.1053 1.0000
8.250 1.3771 0.01700 0.01056 -0.1280 0.0924 1.0000
8.500 1.3882 0.01782 0.01133 -0.1258 0.0803 1.0000
8.750 1.3929 0.01904 0.01242 -0.1229 0.0569 1.0000
9.000 1.4029 0.02002 0.01336 -0.1207 0.0479 1.0000
9.250 1.4149 0.02091 0.01425 -0.1189 0.0438 1.0000
9.500 1.4279 0.02177 0.01513 -0.1173 0.0403 1.0000
9.750 1.4425 0.02255 0.01595 -0.1159 0.0386 1.0000
10.000 1.4560 0.02342 0.01685 -0.1145 0.0365 1.0000
10.250 1.4680 0.02443 0.01786 -0.1129 0.0342 1.0000
10.500 1.4801 0.02544 0.01891 -0.1115 0.0317 1.0000
10.750 1.4935 0.02639 0.01989 -0.1102 0.0295 1.0000
11.000 1.5034 0.02762 0.02111 -0.1086 0.0252 1.0000
11.250 1.5123 0.02897 0.02244 -0.1070 0.0198 1.0000
11.500 1.5204 0.03042 0.02387 -0.1055 0.0155 1.0000
11.750 1.5293 0.03184 0.02530 -0.1041 0.0130 1.0000
12.000 1.5381 0.03331 0.02680 -0.1027 0.0109 1.0000
12.250 1.5467 0.03483 0.02836 -0.1014 0.0093 1.0000
12.500 1.5554 0.03638 0.02993 -0.1002 0.0078 1.0000
12.750 1.5638 0.03798 0.03158 -0.0990 0.0067 1.0000
13.000 1.5718 0.03967 0.03330 -0.0979 0.0056 1.0000
13.250 1.5799 0.04139 0.03506 -0.0969 0.0049 1.0000
13.500 1.5880 0.04315 0.03687 -0.0960 0.0043 1.0000
13.750 1.5952 0.04503 0.03880 -0.0950 0.0038 1.0000
14.000 1.6025 0.04695 0.04078 -0.0942 0.0035 1.0000
14.250 1.6099 0.04889 0.04278 -0.0934 0.0032 1.0000
14.500 1.6162 0.05100 0.04495 -0.0927 0.0029 1.0000
14.750 1.6219 0.05321 0.04722 -0.0920 0.0027 1.0000
15.000 1.6273 0.05550 0.04957 -0.0914 0.0025 1.0000
15.250 1.6326 0.05785 0.05199 -0.0909 0.0023 1.0000
15.500 1.6382 0.06021 0.05442 -0.0905 0.0022 1.0000
15.750 1.6427 0.06275 0.05704 -0.0901 0.0021 1.0000
16.000 1.6467 0.06541 0.05977 -0.0899 0.0020 1.0000
16.250 1.6501 0.06817 0.06261 -0.0897 0.0019 1.0000
16.500 1.6525 0.07113 0.06565 -0.0896 0.0017 1.0000
16.750 1.6540 0.07427 0.06886 -0.0896 0.0016 1.0000
17.000 1.6551 0.07753 0.07221 -0.0897 0.0015 1.0000
17.250 1.6553 0.08097 0.07574 -0.0900 0.0015 1.0000
17.500 1.6560 0.08439 0.07924 -0.0903 0.0014 1.0000
17.750 1.6562 0.08794 0.08289 -0.0908 0.0014 1.0000
18.000 1.6559 0.09162 0.08666 -0.0914 0.0013 1.0000
18.250 1.6550 0.09545 0.09059 -0.0921 0.0013 1.0000
18.500 1.6532 0.09948 0.09472 -0.0931 0.0013 1.0000
18.750 1.6506 0.10367 0.09902 -0.0941 0.0012 1.0000
19.000 1.6477 0.10796 0.10340 -0.0953 0.0012 1.0000
19.250 1.6442 0.11240 0.10795 -0.0967 0.0011 1.0000
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