EPPLER 397 AIRFOIL (e397-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 397 AIRFOIL (e397-il) Reynolds number: 1,000,000 Max Cl/Cd: 169.21 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e397-il-1000000.txt Download as CSV file: xf-e397-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -0.4658 0.11680 0.11494 -0.0576 1.0000 0.0042
-14.500 -0.4963 0.10498 0.10299 -0.0640 0.9995 0.0041
-14.250 -0.5129 0.09564 0.09351 -0.0706 0.9987 0.0039
-14.000 -0.5270 0.08686 0.08463 -0.0774 0.9975 0.0039
-13.750 -0.5381 0.07866 0.07633 -0.0844 0.9959 0.0039
-13.500 -0.5484 0.07063 0.06817 -0.0920 0.9940 0.0038
-13.250 -0.5649 0.06227 0.05970 -0.0997 0.9904 0.0038
-13.000 -0.5733 0.05477 0.05208 -0.1078 0.9859 0.0037
-12.750 -0.5834 0.04715 0.04433 -0.1161 0.9787 0.0037
-12.500 -0.5975 0.03900 0.03601 -0.1250 0.9631 0.0037
-12.250 -0.5858 0.03092 0.02769 -0.1391 0.9505 0.0038
-12.000 -0.5524 0.02408 0.02051 -0.1566 0.9335 0.0038
-11.750 -0.5328 0.02162 0.01777 -0.1614 0.9120 0.0038
-11.500 -0.5196 0.02022 0.01617 -0.1618 0.8943 0.0039
-11.250 -0.5043 0.01910 0.01489 -0.1617 0.8807 0.0040
-10.750 -0.4676 0.01724 0.01273 -0.1613 0.8595 0.0044
-10.500 -0.4467 0.01647 0.01181 -0.1612 0.8508 0.0046
-10.250 -0.4249 0.01571 0.01093 -0.1611 0.8424 0.0047
-10.000 -0.4011 0.01518 0.01028 -0.1610 0.8351 0.0050
-9.750 -0.3796 0.01413 0.00907 -0.1611 0.8277 0.0054
-9.500 -0.3550 0.01354 0.00838 -0.1611 0.8216 0.0059
-9.250 -0.3295 0.01306 0.00782 -0.1612 0.8152 0.0065
-9.000 -0.3036 0.01265 0.00729 -0.1612 0.8093 0.0070
-8.750 -0.2780 0.01202 0.00659 -0.1614 0.8037 0.0082
-8.500 -0.2513 0.01162 0.00612 -0.1616 0.7982 0.0095
-8.250 -0.2248 0.01120 0.00562 -0.1617 0.7932 0.0119
-8.000 -0.1976 0.01078 0.00517 -0.1619 0.7885 0.0155
-7.750 -0.1703 0.01043 0.00480 -0.1621 0.7835 0.0198
-7.500 -0.1429 0.01016 0.00450 -0.1623 0.7787 0.0242
-7.250 -0.1150 0.00988 0.00421 -0.1626 0.7745 0.0291
-7.000 -0.0870 0.00961 0.00394 -0.1629 0.7701 0.0345
-6.750 -0.0591 0.00937 0.00369 -0.1631 0.7658 0.0413
-6.500 -0.0310 0.00917 0.00347 -0.1633 0.7616 0.0486
-6.250 -0.0026 0.00895 0.00326 -0.1636 0.7577 0.0569
-6.000 0.0257 0.00874 0.00307 -0.1639 0.7537 0.0680
-5.750 0.0540 0.00855 0.00289 -0.1642 0.7498 0.0799
-5.500 0.0825 0.00840 0.00273 -0.1645 0.7460 0.0908
-5.250 0.1112 0.00821 0.00258 -0.1648 0.7425 0.1035
-5.000 0.1398 0.00805 0.00244 -0.1651 0.7388 0.1176
-4.750 0.1684 0.00792 0.00231 -0.1654 0.7352 0.1321
-4.500 0.1971 0.00782 0.00221 -0.1657 0.7315 0.1469
-4.250 0.2260 0.00768 0.00211 -0.1660 0.7283 0.1618
-4.000 0.2548 0.00756 0.00202 -0.1663 0.7249 0.1775
-3.500 0.3123 0.00740 0.00188 -0.1668 0.7179 0.2105
-3.250 0.3412 0.00732 0.00183 -0.1671 0.7148 0.2267
-3.000 0.3701 0.00724 0.00178 -0.1674 0.7116 0.2424
-2.750 0.3990 0.00717 0.00174 -0.1677 0.7082 0.2588
-2.500 0.4277 0.00713 0.00171 -0.1680 0.7049 0.2752
-2.250 0.4566 0.00713 0.00169 -0.1682 0.7014 0.2903
-2.000 0.4854 0.00706 0.00168 -0.1685 0.6986 0.3064
-1.750 0.5142 0.00701 0.00166 -0.1688 0.6953 0.3217
-1.500 0.5430 0.00698 0.00165 -0.1690 0.6921 0.3380
-1.250 0.5716 0.00697 0.00165 -0.1692 0.6888 0.3534
-1.000 0.6004 0.00697 0.00167 -0.1695 0.6855 0.3703
-0.750 0.6291 0.00693 0.00168 -0.1698 0.6824 0.3873
-0.500 0.6578 0.00690 0.00170 -0.1700 0.6790 0.4054
-0.250 0.6864 0.00689 0.00172 -0.1702 0.6757 0.4237
0.000 0.7149 0.00691 0.00175 -0.1704 0.6721 0.4429
0.250 0.7435 0.00689 0.00179 -0.1706 0.6689 0.4625
0.500 0.7719 0.00686 0.00183 -0.1708 0.6652 0.4834
0.750 0.8003 0.00686 0.00187 -0.1710 0.6614 0.5050
1.000 0.8284 0.00688 0.00192 -0.1711 0.6574 0.5271
1.250 0.8567 0.00688 0.00198 -0.1713 0.6536 0.5506
1.500 0.8849 0.00685 0.00204 -0.1715 0.6494 0.5748
1.750 0.9128 0.00686 0.00210 -0.1715 0.6450 0.6005
2.000 0.9405 0.00690 0.00217 -0.1716 0.6403 0.6261
2.250 0.9685 0.00687 0.00225 -0.1717 0.6355 0.6527
2.500 0.9958 0.00688 0.00232 -0.1716 0.6299 0.6803
2.750 1.0229 0.00691 0.00240 -0.1715 0.6240 0.7087
3.000 1.0497 0.00691 0.00248 -0.1713 0.6159 0.7381
3.250 1.0756 0.00693 0.00257 -0.1710 0.6065 0.7689
3.500 1.1008 0.00698 0.00266 -0.1705 0.5967 0.8028
3.750 1.1263 0.00699 0.00277 -0.1700 0.5881 0.8399
4.000 1.1487 0.00701 0.00288 -0.1688 0.5793 0.8857
4.250 1.1685 0.00692 0.00292 -0.1670 0.5707 1.0000
4.500 1.1946 0.00706 0.00303 -0.1667 0.5606 1.0000
4.750 1.2197 0.00723 0.00317 -0.1663 0.5483 1.0000
5.000 1.2444 0.00742 0.00331 -0.1658 0.5361 1.0000
5.250 1.2691 0.00761 0.00347 -0.1653 0.5226 1.0000
5.500 1.2925 0.00784 0.00366 -0.1646 0.5070 1.0000
5.750 1.3149 0.00811 0.00387 -0.1637 0.4888 1.0000
6.000 1.3356 0.00845 0.00412 -0.1624 0.4657 1.0000
6.250 1.3538 0.00888 0.00443 -0.1608 0.4379 1.0000
6.500 1.3701 0.00938 0.00479 -0.1587 0.4078 1.0000
6.750 1.3830 0.00994 0.00519 -0.1561 0.3754 1.0000
7.000 1.3934 0.01054 0.00564 -0.1529 0.3444 1.0000
7.250 1.4008 0.01126 0.00618 -0.1493 0.3095 1.0000
7.500 1.4078 0.01203 0.00677 -0.1457 0.2749 1.0000
7.750 1.4150 0.01282 0.00740 -0.1423 0.2433 1.0000
8.000 1.4231 0.01360 0.00804 -0.1391 0.2172 1.0000
8.250 1.4297 0.01448 0.00878 -0.1359 0.1907 1.0000
8.500 1.4349 0.01546 0.00962 -0.1325 0.1640 1.0000
8.750 1.4416 0.01643 0.01048 -0.1295 0.1410 1.0000
9.000 1.4461 0.01757 0.01150 -0.1263 0.1175 1.0000
9.250 1.4505 0.01880 0.01260 -0.1233 0.0969 1.0000
9.500 1.4570 0.01997 0.01369 -0.1208 0.0794 1.0000
9.750 1.4586 0.02151 0.01509 -0.1177 0.0568 1.0000
10.000 1.4675 0.02266 0.01622 -0.1157 0.0495 1.0000
10.250 1.4790 0.02367 0.01725 -0.1140 0.0467 1.0000
10.500 1.4885 0.02486 0.01845 -0.1122 0.0432 1.0000
10.750 1.4990 0.02601 0.01963 -0.1106 0.0403 1.0000
11.000 1.5134 0.02689 0.02058 -0.1095 0.0390 1.0000
11.250 1.5251 0.02800 0.02171 -0.1081 0.0364 1.0000
11.500 1.5337 0.02938 0.02311 -0.1065 0.0331 1.0000
11.750 1.5461 0.03049 0.02425 -0.1054 0.0306 1.0000
12.000 1.5548 0.03191 0.02565 -0.1040 0.0257 1.0000
12.250 1.5624 0.03348 0.02720 -0.1025 0.0205 1.0000
12.500 1.5684 0.03523 0.02894 -0.1011 0.0163 1.0000
12.750 1.5757 0.03692 0.03065 -0.0998 0.0138 1.0000
13.000 1.5822 0.03872 0.03248 -0.0985 0.0117 1.0000
13.250 1.5883 0.04061 0.03441 -0.0973 0.0101 1.0000
13.500 1.5953 0.04246 0.03631 -0.0963 0.0088 1.0000
13.750 1.6008 0.04449 0.03838 -0.0952 0.0077 1.0000
14.000 1.6065 0.04657 0.04052 -0.0943 0.0068 1.0000
14.250 1.6125 0.04865 0.04266 -0.0934 0.0060 1.0000
14.500 1.6147 0.05122 0.04528 -0.0925 0.0052 1.0000
14.750 1.6213 0.05335 0.04748 -0.0918 0.0049 1.0000
15.000 1.6266 0.05565 0.04985 -0.0912 0.0045 1.0000
15.250 1.6300 0.05824 0.05252 -0.0907 0.0042 1.0000
15.500 1.6313 0.06115 0.05550 -0.0902 0.0039 1.0000
15.750 1.6325 0.06416 0.05859 -0.0898 0.0036 1.0000
16.000 1.6359 0.06693 0.06145 -0.0896 0.0034 1.0000
16.250 1.6378 0.06994 0.06456 -0.0894 0.0033 1.0000
16.500 1.6401 0.07297 0.06767 -0.0894 0.0031 1.0000
16.750 1.6407 0.07629 0.07107 -0.0895 0.0029 1.0000
17.000 1.6397 0.07992 0.07479 -0.0897 0.0028 1.0000
17.250 1.6367 0.08390 0.07887 -0.0901 0.0027 1.0000
17.500 1.6301 0.08853 0.08362 -0.0908 0.0025 1.0000
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