EPPLER 396 AIRFOIL (e396-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 396 AIRFOIL (e396-il) Reynolds number: 1,000,000 Max Cl/Cd: 169.27 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e396-il-1000000.txt Download as CSV file: xf-e396-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.4102 0.10476 0.10298 -0.0655 0.9976 0.0045
-13.250 -0.4725 0.08534 0.08332 -0.0778 0.9959 0.0043
-13.000 -0.4889 0.07556 0.07344 -0.0863 0.9941 0.0043
-12.750 -0.5165 0.06479 0.06250 -0.0958 0.9899 0.0041
-12.500 -0.5276 0.05617 0.05377 -0.1052 0.9855 0.0042
-12.250 -0.5407 0.04791 0.04535 -0.1140 0.9763 0.0039
-12.000 -0.5544 0.03845 0.03570 -0.1254 0.9603 0.0039
-11.750 -0.5337 0.02714 0.02402 -0.1483 0.9456 0.0040
-11.500 -0.5026 0.02278 0.01935 -0.1596 0.9277 0.0042
-11.250 -0.4832 0.02102 0.01735 -0.1618 0.9097 0.0043
-11.000 -0.4659 0.01968 0.01582 -0.1624 0.8946 0.0044
-10.750 -0.4458 0.01878 0.01478 -0.1625 0.8827 0.0047
-10.500 -0.4259 0.01781 0.01363 -0.1626 0.8718 0.0049
-10.250 -0.4049 0.01693 0.01259 -0.1626 0.8619 0.0050
-10.000 -0.3824 0.01617 0.01168 -0.1626 0.8535 0.0052
-9.750 -0.3586 0.01556 0.01094 -0.1626 0.8454 0.0054
-9.500 -0.3344 0.01493 0.01020 -0.1626 0.8380 0.0055
-9.250 -0.3121 0.01376 0.00882 -0.1628 0.8306 0.0059
-9.000 -0.2869 0.01307 0.00802 -0.1630 0.8241 0.0062
-8.750 -0.2611 0.01254 0.00740 -0.1631 0.8178 0.0067
-8.500 -0.2346 0.01210 0.00685 -0.1632 0.8120 0.0072
-8.250 -0.2077 0.01168 0.00635 -0.1633 0.8060 0.0077
-8.000 -0.1810 0.01116 0.00570 -0.1635 0.8007 0.0090
-7.750 -0.1536 0.01075 0.00525 -0.1637 0.7954 0.0108
-7.500 -0.1263 0.01031 0.00478 -0.1639 0.7901 0.0144
-7.250 -0.0988 0.00998 0.00442 -0.1641 0.7853 0.0194
-7.000 -0.0708 0.00968 0.00412 -0.1644 0.7805 0.0247
-6.750 -0.0428 0.00949 0.00389 -0.1646 0.7756 0.0288
-6.500 -0.0148 0.00925 0.00363 -0.1648 0.7711 0.0351
-6.250 0.0136 0.00902 0.00340 -0.1650 0.7667 0.0414
-6.000 0.0419 0.00885 0.00321 -0.1652 0.7621 0.0472
-5.750 0.0701 0.00864 0.00299 -0.1655 0.7578 0.0568
-5.500 0.0987 0.00844 0.00281 -0.1658 0.7538 0.0674
-5.250 0.1272 0.00826 0.00265 -0.1660 0.7494 0.0787
-5.000 0.1557 0.00813 0.00250 -0.1662 0.7453 0.0894
-4.750 0.1843 0.00800 0.00236 -0.1665 0.7414 0.1018
-4.500 0.2131 0.00784 0.00224 -0.1668 0.7374 0.1156
-4.250 0.2418 0.00772 0.00213 -0.1670 0.7334 0.1290
-4.000 0.2703 0.00763 0.00203 -0.1673 0.7295 0.1436
-3.750 0.2991 0.00751 0.00195 -0.1675 0.7258 0.1601
-3.500 0.3280 0.00740 0.00187 -0.1678 0.7219 0.1757
-3.250 0.3566 0.00732 0.00181 -0.1680 0.7180 0.1933
-3.000 0.3853 0.00727 0.00176 -0.1683 0.7141 0.2113
-2.750 0.4141 0.00719 0.00171 -0.1685 0.7105 0.2280
-2.250 0.4715 0.00707 0.00164 -0.1690 0.7026 0.2626
-2.000 0.5001 0.00705 0.00162 -0.1692 0.6987 0.2798
-1.750 0.5289 0.00698 0.00161 -0.1694 0.6949 0.2983
-1.500 0.5575 0.00694 0.00160 -0.1696 0.6909 0.3153
-1.250 0.5860 0.00693 0.00159 -0.1698 0.6869 0.3342
-1.000 0.6146 0.00690 0.00160 -0.1700 0.6830 0.3533
-0.750 0.6432 0.00685 0.00161 -0.1702 0.6789 0.3740
-0.500 0.6717 0.00684 0.00162 -0.1704 0.6748 0.3941
-0.250 0.7000 0.00684 0.00165 -0.1706 0.6706 0.4166
0.000 0.7285 0.00681 0.00168 -0.1708 0.6666 0.4400
0.250 0.7570 0.00678 0.00171 -0.1710 0.6622 0.4646
0.500 0.7851 0.00678 0.00175 -0.1711 0.6578 0.4895
0.750 0.8134 0.00678 0.00180 -0.1712 0.6534 0.5161
1.000 0.8417 0.00675 0.00185 -0.1714 0.6486 0.5441
1.250 0.8696 0.00676 0.00191 -0.1715 0.6437 0.5728
1.500 0.8976 0.00676 0.00198 -0.1716 0.6388 0.6030
2.000 0.9529 0.00678 0.00212 -0.1716 0.6280 0.6666
2.250 0.9807 0.00676 0.00221 -0.1717 0.6224 0.7009
2.500 1.0078 0.00677 0.00230 -0.1715 0.6158 0.7364
2.750 1.0345 0.00679 0.00240 -0.1713 0.6092 0.7738
3.000 1.0606 0.00679 0.00250 -0.1710 0.6021 0.8151
3.250 1.0851 0.00679 0.00260 -0.1703 0.5955 0.8621
3.500 1.1044 0.00672 0.00267 -0.1683 0.5882 0.9319
3.750 1.1305 0.00676 0.00272 -0.1680 0.5802 1.0000
4.000 1.1570 0.00689 0.00282 -0.1678 0.5714 1.0000
4.250 1.1838 0.00701 0.00294 -0.1677 0.5631 1.0000
4.500 1.2095 0.00717 0.00306 -0.1674 0.5542 1.0000
4.750 1.2357 0.00730 0.00318 -0.1671 0.5441 1.0000
5.000 1.2611 0.00747 0.00332 -0.1668 0.5328 1.0000
5.250 1.2860 0.00765 0.00349 -0.1663 0.5212 1.0000
5.500 1.3103 0.00786 0.00366 -0.1657 0.5091 1.0000
5.750 1.3341 0.00809 0.00384 -0.1651 0.4963 1.0000
6.000 1.3574 0.00833 0.00405 -0.1643 0.4817 1.0000
6.250 1.3797 0.00861 0.00428 -0.1634 0.4639 1.0000
6.500 1.4013 0.00891 0.00453 -0.1623 0.4459 1.0000
6.750 1.4205 0.00931 0.00483 -0.1609 0.4239 1.0000
7.000 1.4393 0.00971 0.00514 -0.1593 0.4005 1.0000
7.250 1.4549 0.01020 0.00552 -0.1572 0.3738 1.0000
7.500 1.4659 0.01079 0.00596 -0.1542 0.3428 1.0000
7.750 1.4759 0.01144 0.00646 -0.1510 0.3127 1.0000
8.000 1.4847 0.01215 0.00702 -0.1478 0.2827 1.0000
8.250 1.4931 0.01291 0.00763 -0.1445 0.2538 1.0000
8.500 1.5001 0.01376 0.00832 -0.1412 0.2252 1.0000
8.750 1.5067 0.01465 0.00908 -0.1379 0.1982 1.0000
9.000 1.5139 0.01555 0.00987 -0.1348 0.1747 1.0000
9.250 1.5203 0.01654 0.01074 -0.1318 0.1538 1.0000
9.500 1.5276 0.01753 0.01166 -0.1290 0.1345 1.0000
9.750 1.5328 0.01870 0.01272 -0.1260 0.1152 1.0000
10.000 1.5389 0.01987 0.01381 -0.1234 0.0983 1.0000
10.250 1.5439 0.02117 0.01503 -0.1207 0.0818 1.0000
10.500 1.5488 0.02255 0.01634 -0.1182 0.0676 1.0000
10.750 1.5546 0.02394 0.01767 -0.1160 0.0559 1.0000
11.000 1.5612 0.02533 0.01903 -0.1139 0.0466 1.0000
11.250 1.5679 0.02676 0.02044 -0.1119 0.0385 1.0000
11.500 1.5741 0.02829 0.02195 -0.1101 0.0317 1.0000
11.750 1.5804 0.02985 0.02351 -0.1083 0.0265 1.0000
12.000 1.5879 0.03137 0.02504 -0.1068 0.0222 1.0000
12.250 1.5939 0.03307 0.02674 -0.1052 0.0187 1.0000
12.500 1.6011 0.03470 0.02841 -0.1038 0.0159 1.0000
12.750 1.6066 0.03653 0.03025 -0.1024 0.0135 1.0000
13.000 1.6143 0.03822 0.03199 -0.1012 0.0119 1.0000
13.250 1.6198 0.04016 0.03396 -0.1000 0.0102 1.0000
13.500 1.6254 0.04215 0.03600 -0.0989 0.0088 1.0000
13.750 1.6314 0.04414 0.03804 -0.0979 0.0077 1.0000
14.000 1.6338 0.04656 0.04049 -0.0968 0.0063 1.0000
14.250 1.6399 0.04866 0.04267 -0.0960 0.0057 1.0000
14.500 1.6439 0.05103 0.04511 -0.0952 0.0050 1.0000
14.750 1.6443 0.05388 0.04802 -0.0944 0.0042 1.0000
15.000 1.6478 0.05644 0.05066 -0.0938 0.0038 1.0000
15.250 1.6516 0.05902 0.05331 -0.0933 0.0035 1.0000
15.500 1.6541 0.06182 0.05619 -0.0929 0.0032 1.0000
15.750 1.6546 0.06494 0.05939 -0.0926 0.0029 1.0000
16.000 1.6515 0.06863 0.06318 -0.0924 0.0027 1.0000
16.250 1.6489 0.07235 0.06701 -0.0924 0.0025 1.0000
16.500 1.6503 0.07559 0.07034 -0.0925 0.0024 1.0000
16.750 1.6508 0.07902 0.07386 -0.0928 0.0023 1.0000
17.000 1.6504 0.08263 0.07757 -0.0931 0.0022 1.0000
17.250 1.6488 0.08648 0.08153 -0.0936 0.0021 1.0000
17.500 1.6467 0.09049 0.08564 -0.0943 0.0021 1.0000
17.750 1.6439 0.09468 0.08993 -0.0952 0.0020 1.0000
18.000 1.6406 0.09901 0.09436 -0.0961 0.0019 1.0000
18.250 1.6363 0.10353 0.09899 -0.0973 0.0019 1.0000
18.500 1.6315 0.10822 0.10378 -0.0987 0.0018 1.0000
18.750 1.6257 0.11314 0.10880 -0.1003 0.0018 1.0000
19.000 1.6189 0.11830 0.11408 -0.1021 0.0017 1.0000
19.250 1.6111 0.12370 0.11959 -0.1041 0.0017 1.0000
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Polar data table (+)
Polar graphs
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