EPPLER 396 AIRFOIL (e396-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 396 AIRFOIL (e396-il) Reynolds number: 200,000 Max Cl/Cd: 89.3 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e396-il-200000.txt Download as CSV file: xf-e396-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.1904 0.08819 0.08488 -0.0911 0.9624 0.0383
-9.250 -0.1782 0.08221 0.07887 -0.0960 0.9592 0.0337
-9.000 -0.2545 0.05343 0.05007 -0.1210 0.9450 0.0261
-8.750 -0.2685 0.03872 0.03468 -0.1459 0.9306 0.0251
-8.500 -0.2638 0.03372 0.02911 -0.1500 0.9199 0.0254
-8.250 -0.2356 0.02930 0.02403 -0.1552 0.9167 0.0264
-8.000 -0.2185 0.02717 0.02147 -0.1553 0.9082 0.0276
-7.750 -0.1886 0.02456 0.01864 -0.1579 0.9046 0.0310
-7.500 -0.1524 0.02335 0.01715 -0.1604 0.9021 0.0359
-7.250 -0.1343 0.02165 0.01531 -0.1597 0.8943 0.0402
-7.000 -0.1013 0.02062 0.01403 -0.1613 0.8905 0.0485
-6.750 -0.0661 0.01985 0.01314 -0.1632 0.8877 0.0582
-6.500 -0.0455 0.01911 0.01241 -0.1625 0.8804 0.0662
-6.250 -0.0144 0.01828 0.01146 -0.1635 0.8763 0.0764
-6.000 0.0195 0.01755 0.01061 -0.1649 0.8733 0.0880
-5.750 0.0422 0.01734 0.01028 -0.1642 0.8665 0.0985
-5.500 0.0723 0.01679 0.00969 -0.1649 0.8622 0.1125
-5.250 0.1051 0.01618 0.00906 -0.1660 0.8590 0.1287
-5.000 0.1284 0.01595 0.00886 -0.1655 0.8526 0.1442
-4.750 0.1578 0.01562 0.00852 -0.1660 0.8481 0.1621
-4.500 0.1902 0.01532 0.00815 -0.1669 0.8448 0.1833
-4.250 0.2146 0.01520 0.00805 -0.1665 0.8389 0.2022
-4.000 0.2432 0.01502 0.00789 -0.1668 0.8342 0.2234
-3.750 0.2748 0.01480 0.00762 -0.1676 0.8308 0.2463
-3.500 0.3005 0.01475 0.00761 -0.1673 0.8254 0.2673
-3.250 0.3281 0.01467 0.00752 -0.1674 0.8204 0.2899
-3.000 0.3591 0.01451 0.00737 -0.1680 0.8168 0.3131
-2.750 0.3864 0.01448 0.00734 -0.1680 0.8122 0.3358
-2.500 0.4125 0.01446 0.00736 -0.1678 0.8068 0.3582
-2.250 0.4429 0.01434 0.00725 -0.1682 0.8030 0.3826
-2.000 0.4723 0.01429 0.00720 -0.1685 0.7992 0.4082
-1.750 0.4965 0.01433 0.00733 -0.1680 0.7932 0.4314
-1.500 0.5262 0.01425 0.00727 -0.1683 0.7891 0.4582
-1.250 0.5578 0.01415 0.00719 -0.1689 0.7861 0.4875
-1.000 0.5800 0.01427 0.00742 -0.1680 0.7796 0.5150
-0.750 0.6088 0.01421 0.00742 -0.1682 0.7752 0.5459
-0.500 0.6397 0.01411 0.00737 -0.1686 0.7720 0.5792
-0.250 0.6620 0.01423 0.00763 -0.1676 0.7657 0.6116
0.000 0.6896 0.01420 0.00768 -0.1674 0.7611 0.6488
0.250 0.7192 0.01409 0.00765 -0.1675 0.7577 0.6877
0.500 0.7398 0.01422 0.00793 -0.1661 0.7515 0.7268
0.750 0.7641 0.01417 0.00799 -0.1651 0.7467 0.7706
1.000 0.7892 0.01404 0.00793 -0.1640 0.7432 0.8192
1.250 0.8016 0.01410 0.00816 -0.1606 0.7368 0.8780
1.500 0.8290 0.01390 0.00800 -0.1601 0.7320 1.0000
1.750 0.8640 0.01393 0.00790 -0.1616 0.7285 1.0000
2.000 0.8878 0.01422 0.00821 -0.1613 0.7217 1.0000
2.250 0.9186 0.01428 0.00821 -0.1619 0.7169 1.0000
2.500 0.9507 0.01435 0.00820 -0.1627 0.7129 1.0000
2.750 0.9739 0.01461 0.00850 -0.1621 0.7058 1.0000
3.000 1.0052 0.01463 0.00847 -0.1627 0.7012 1.0000
3.250 1.0312 0.01483 0.00867 -0.1625 0.6951 1.0000
3.500 1.0588 0.01493 0.00877 -0.1625 0.6890 1.0000
3.750 1.0920 0.01491 0.00870 -0.1634 0.6848 1.0000
4.000 1.1131 0.01517 0.00904 -0.1623 0.6767 1.0000
4.250 1.1446 0.01514 0.00896 -0.1629 0.6714 1.0000
4.500 1.1675 0.01533 0.00923 -0.1620 0.6633 1.0000
4.750 1.1980 0.01528 0.00916 -0.1624 0.6572 1.0000
5.000 1.2210 0.01546 0.00940 -0.1615 0.6489 1.0000
5.250 1.2513 0.01541 0.00933 -0.1618 0.6424 1.0000
5.500 1.2730 0.01557 0.00958 -0.1607 0.6332 1.0000
5.750 1.3022 0.01554 0.00954 -0.1608 0.6257 1.0000
6.000 1.3245 0.01565 0.00973 -0.1597 0.6161 1.0000
6.250 1.3481 0.01576 0.00989 -0.1589 0.6068 1.0000
6.500 1.3753 0.01575 0.00989 -0.1586 0.5975 1.0000
6.750 1.3960 0.01587 0.01007 -0.1572 0.5860 1.0000
7.000 1.4166 0.01601 0.01029 -0.1558 0.5741 1.0000
7.250 1.4374 0.01616 0.01048 -0.1544 0.5618 1.0000
7.500 1.4574 0.01632 0.01069 -0.1529 0.5486 1.0000
7.750 1.4754 0.01653 0.01095 -0.1510 0.5336 1.0000
8.000 1.4919 0.01678 0.01122 -0.1489 0.5173 1.0000
8.250 1.5067 0.01709 0.01153 -0.1465 0.4997 1.0000
8.500 1.5186 0.01748 0.01192 -0.1436 0.4812 1.0000
8.750 1.5252 0.01795 0.01240 -0.1398 0.4610 1.0000
9.000 1.5311 0.01855 0.01294 -0.1360 0.4396 1.0000
9.250 1.5343 0.01930 0.01366 -0.1320 0.4154 1.0000
9.500 1.5356 0.02023 0.01455 -0.1279 0.3898 1.0000
9.750 1.5344 0.02139 0.01562 -0.1238 0.3624 1.0000
10.000 1.5315 0.02279 0.01690 -0.1197 0.3343 1.0000
10.250 1.5273 0.02443 0.01842 -0.1158 0.3063 1.0000
10.500 1.5225 0.02629 0.02016 -0.1122 0.2791 1.0000
10.750 1.5177 0.02832 0.02209 -0.1089 0.2530 1.0000
11.000 1.5133 0.03050 0.02417 -0.1059 0.2273 1.0000
11.250 1.5090 0.03282 0.02639 -0.1033 0.2032 1.0000
11.500 1.5039 0.03534 0.02881 -0.1008 0.1809 1.0000
11.750 1.5001 0.03789 0.03129 -0.0987 0.1585 1.0000
12.000 1.4954 0.04066 0.03397 -0.0968 0.1384 1.0000
12.250 1.4917 0.04348 0.03672 -0.0951 0.1192 1.0000
12.500 1.4864 0.04658 0.03974 -0.0935 0.1027 1.0000
13.000 1.4759 0.05318 0.04626 -0.0909 0.0763 1.0000
13.250 1.4725 0.05648 0.04956 -0.0900 0.0657 1.0000
13.500 1.4699 0.05980 0.05293 -0.0891 0.0569 1.0000
13.750 1.4646 0.06353 0.05668 -0.0884 0.0504 1.0000
14.000 1.4615 0.06711 0.06030 -0.0880 0.0448 1.0000
14.250 1.4570 0.07096 0.06423 -0.0876 0.0401 1.0000
14.500 1.4562 0.07445 0.06780 -0.0875 0.0358 1.0000
14.750 1.4478 0.07893 0.07227 -0.0872 0.0326 1.0000
15.000 1.4499 0.08221 0.07572 -0.0873 0.0294 1.0000
15.250 1.4486 0.08598 0.07957 -0.0876 0.0268 1.0000
15.500 1.4428 0.09023 0.08381 -0.0875 0.0244 1.0000
15.750 1.4446 0.09367 0.08744 -0.0878 0.0227 1.0000
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Polar data table (+)
Polar graphs
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