EPPLER 396 AIRFOIL (e396-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: EPPLER 396 AIRFOIL (e396-il) Reynolds number: 200,000 Max Cl/Cd: 90.29 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e396-il-200000-n5.txt Download as CSV file: xf-e396-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.3649 0.06134 0.05753 -0.1026 0.9488 0.0111
-10.500 -0.3803 0.05080 0.04677 -0.1147 0.9374 0.0110
-10.250 -0.3826 0.04202 0.03770 -0.1272 0.9252 0.0110
-10.000 -0.3764 0.03446 0.02973 -0.1408 0.9110 0.0111
-9.750 -0.3579 0.03061 0.02546 -0.1473 0.9020 0.0113
-9.500 -0.3429 0.02794 0.02256 -0.1501 0.8919 0.0117
-9.250 -0.3205 0.02601 0.02041 -0.1524 0.8847 0.0123
-9.000 -0.2984 0.02447 0.01866 -0.1537 0.8769 0.0129
-8.750 -0.2741 0.02300 0.01695 -0.1550 0.8705 0.0140
-8.500 -0.2507 0.02181 0.01548 -0.1555 0.8634 0.0154
-8.250 -0.2241 0.02068 0.01422 -0.1568 0.8581 0.0175
-8.000 -0.2002 0.01987 0.01326 -0.1570 0.8510 0.0201
-7.750 -0.1736 0.01882 0.01205 -0.1578 0.8456 0.0230
-7.500 -0.1475 0.01814 0.01122 -0.1581 0.8399 0.0269
-7.250 -0.1212 0.01745 0.01045 -0.1585 0.8341 0.0319
-7.000 -0.0925 0.01689 0.00972 -0.1591 0.8297 0.0380
-6.750 -0.0667 0.01641 0.00917 -0.1593 0.8238 0.0445
-6.500 -0.0392 0.01590 0.00858 -0.1596 0.8188 0.0514
-6.250 -0.0102 0.01552 0.00803 -0.1601 0.8146 0.0590
-6.000 0.0161 0.01509 0.00760 -0.1602 0.8090 0.0676
-5.750 0.0440 0.01472 0.00716 -0.1605 0.8043 0.0772
-5.500 0.0733 0.01440 0.00673 -0.1610 0.8004 0.0878
-5.250 0.1000 0.01415 0.00644 -0.1610 0.7950 0.0994
-5.000 0.1280 0.01388 0.00613 -0.1613 0.7904 0.1125
-4.750 0.1572 0.01364 0.00583 -0.1617 0.7866 0.1265
-4.500 0.1845 0.01345 0.00561 -0.1618 0.7816 0.1417
-4.250 0.2124 0.01325 0.00542 -0.1620 0.7770 0.1579
-4.000 0.2413 0.01308 0.00521 -0.1624 0.7731 0.1753
-3.750 0.2694 0.01294 0.00506 -0.1625 0.7687 0.1927
-3.500 0.2970 0.01283 0.00494 -0.1626 0.7639 0.2109
-3.250 0.3256 0.01272 0.00480 -0.1629 0.7599 0.2295
-3.000 0.3546 0.01262 0.00468 -0.1632 0.7561 0.2484
-2.750 0.3817 0.01255 0.00463 -0.1632 0.7512 0.2669
-2.500 0.4099 0.01248 0.00455 -0.1633 0.7469 0.2863
-2.250 0.4390 0.01242 0.00447 -0.1636 0.7433 0.3060
-2.000 0.4664 0.01237 0.00445 -0.1636 0.7387 0.3256
-1.750 0.4941 0.01234 0.00444 -0.1637 0.7341 0.3462
-1.500 0.5226 0.01229 0.00440 -0.1639 0.7302 0.3669
-1.250 0.5509 0.01227 0.00439 -0.1640 0.7263 0.3893
-1.000 0.5779 0.01225 0.00443 -0.1639 0.7213 0.4114
-0.750 0.6060 0.01223 0.00445 -0.1640 0.7171 0.4350
-0.500 0.6350 0.01221 0.00444 -0.1643 0.7135 0.4601
-0.250 0.6612 0.01222 0.00454 -0.1640 0.7083 0.4853
0.000 0.6886 0.01222 0.00460 -0.1640 0.7037 0.5124
0.250 0.7171 0.01221 0.00462 -0.1641 0.6999 0.5410
0.500 0.7434 0.01222 0.00474 -0.1639 0.6949 0.5703
0.750 0.7700 0.01223 0.00484 -0.1636 0.6900 0.6015
1.000 0.7974 0.01223 0.00491 -0.1635 0.6859 0.6344
1.250 0.8229 0.01225 0.00504 -0.1630 0.6809 0.6685
1.500 0.8481 0.01227 0.00517 -0.1624 0.6757 0.7047
1.750 0.8739 0.01226 0.00524 -0.1619 0.6715 0.7432
2.000 0.8969 0.01227 0.00538 -0.1608 0.6662 0.7852
2.250 0.9182 0.01226 0.00548 -0.1592 0.6609 0.8340
2.500 0.9389 0.01216 0.00546 -0.1574 0.6564 0.9042
2.750 0.9661 0.01219 0.00556 -0.1573 0.6505 1.0000
3.000 0.9935 0.01232 0.00567 -0.1574 0.6448 1.0000
3.250 1.0212 0.01246 0.00577 -0.1575 0.6395 1.0000
3.500 1.0470 0.01261 0.00595 -0.1572 0.6327 1.0000
3.750 1.0749 0.01273 0.00604 -0.1573 0.6272 1.0000
4.000 1.0997 0.01290 0.00626 -0.1568 0.6197 1.0000
4.250 1.1266 0.01303 0.00637 -0.1567 0.6133 1.0000
4.500 1.1510 0.01321 0.00660 -0.1561 0.6049 1.0000
4.750 1.1769 0.01335 0.00673 -0.1558 0.5973 1.0000
5.000 1.2008 0.01353 0.00695 -0.1552 0.5880 1.0000
5.250 1.2252 0.01371 0.00715 -0.1546 0.5793 1.0000
5.500 1.2494 0.01390 0.00735 -0.1539 0.5700 1.0000
5.750 1.2718 0.01411 0.00760 -0.1530 0.5591 1.0000
6.000 1.2943 0.01434 0.00786 -0.1521 0.5482 1.0000
6.250 1.3164 0.01458 0.00811 -0.1511 0.5371 1.0000
6.500 1.3374 0.01485 0.00841 -0.1499 0.5247 1.0000
6.750 1.3571 0.01515 0.00871 -0.1485 0.5108 1.0000
7.000 1.3754 0.01549 0.00905 -0.1468 0.4957 1.0000
7.250 1.3924 0.01586 0.00943 -0.1449 0.4796 1.0000
7.500 1.4071 0.01627 0.00984 -0.1426 0.4629 1.0000
7.750 1.4193 0.01675 0.01029 -0.1399 0.4445 1.0000
8.000 1.4290 0.01734 0.01085 -0.1369 0.4239 1.0000
8.250 1.4375 0.01801 0.01148 -0.1338 0.4011 1.0000
8.500 1.4435 0.01884 0.01222 -0.1304 0.3771 1.0000
8.750 1.4474 0.01982 0.01311 -0.1269 0.3523 1.0000
9.000 1.4498 0.02095 0.01415 -0.1234 0.3255 1.0000
9.250 1.4513 0.02225 0.01535 -0.1200 0.2993 1.0000
9.500 1.4521 0.02370 0.01671 -0.1167 0.2739 1.0000
9.750 1.4523 0.02531 0.01822 -0.1137 0.2497 1.0000
10.000 1.4525 0.02704 0.01986 -0.1109 0.2258 1.0000
10.250 1.4533 0.02884 0.02161 -0.1083 0.2032 1.0000
10.500 1.4535 0.03079 0.02348 -0.1059 0.1822 1.0000
10.750 1.4555 0.03270 0.02534 -0.1039 0.1626 1.0000
11.000 1.4570 0.03473 0.02731 -0.1019 0.1445 1.0000
11.250 1.4583 0.03686 0.02939 -0.1001 0.1281 1.0000
11.500 1.4602 0.03901 0.03151 -0.0985 0.1127 1.0000
11.750 1.4623 0.04123 0.03371 -0.0970 0.0987 1.0000
12.000 1.4640 0.04355 0.03601 -0.0956 0.0859 1.0000
12.250 1.4656 0.04596 0.03841 -0.0944 0.0745 1.0000
12.500 1.4668 0.04849 0.04093 -0.0932 0.0642 1.0000
12.750 1.4695 0.05094 0.04345 -0.0922 0.0555 1.0000
13.000 1.4715 0.05353 0.04607 -0.0914 0.0483 1.0000
13.250 1.4719 0.05637 0.04893 -0.0906 0.0422 1.0000
13.500 1.4748 0.05902 0.05166 -0.0899 0.0369 1.0000
13.750 1.4744 0.06212 0.05479 -0.0894 0.0324 1.0000
14.000 1.4769 0.06495 0.05773 -0.0890 0.0287 1.0000
14.250 1.4759 0.06828 0.06111 -0.0887 0.0255 1.0000
14.500 1.4765 0.07149 0.06444 -0.0885 0.0229 1.0000
14.750 1.4770 0.07478 0.06782 -0.0884 0.0204 1.0000
15.000 1.4744 0.07858 0.07169 -0.0886 0.0185 1.0000
15.250 1.4734 0.08223 0.07547 -0.0888 0.0169 1.0000
15.500 1.4730 0.08586 0.07924 -0.0891 0.0154 1.0000
15.750 1.4709 0.08983 0.08330 -0.0897 0.0141 1.0000
16.000 1.4651 0.09445 0.08805 -0.0905 0.0130 1.0000
16.250 1.4630 0.09856 0.09231 -0.0913 0.0122 1.0000
16.500 1.4601 0.10287 0.09677 -0.0923 0.0114 1.0000
16.750 1.4568 0.10730 0.10135 -0.0935 0.0107 1.0000
17.000 1.4532 0.11184 0.10601 -0.0949 0.0101 1.0000
17.250 1.4482 0.11670 0.11098 -0.0966 0.0096 1.0000
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