E385 (8.41%) (e385-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: E385 (8.41%) (e385-il) Reynolds number: 100,000 Max Cl/Cd: 67.24 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e385-il-100000.txt Download as CSV file: xf-e385-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: E385 (8.41%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.2874 0.10699 0.10271 -0.0287 1.0000 0.0584
-7.500 -0.3027 0.10672 0.10256 -0.0254 1.0000 0.0596
-7.250 -0.3182 0.10648 0.10242 -0.0222 1.0000 0.0597
-7.000 -0.3273 0.10572 0.10174 -0.0215 0.9984 0.0612
-6.750 -0.3097 0.10407 0.10010 -0.0330 0.9870 0.0636
-6.500 -0.2711 0.10085 0.09687 -0.0538 0.9737 0.0644
-6.250 -0.2639 0.09403 0.09005 -0.0435 0.9734 0.0663
-6.000 -0.2438 0.09009 0.08611 -0.0451 0.9664 0.0695
-5.750 -0.2144 0.08597 0.08193 -0.0528 0.9591 0.0738
-5.500 -0.1607 0.08201 0.07783 -0.0803 0.9454 0.0785
-5.250 -0.1614 0.07770 0.07361 -0.0719 0.9390 0.0801
-5.000 -0.1395 0.07413 0.07003 -0.0724 0.9334 0.0838
-4.500 -0.0692 0.06539 0.06114 -0.0909 0.9186 0.0955
-4.250 -0.0486 0.06261 0.05832 -0.0925 0.9106 0.1012
-4.000 -0.0015 0.05768 0.05325 -0.1037 0.9050 0.1108
-3.750 0.0429 0.05360 0.04897 -0.1130 0.8989 0.1240
-3.500 0.0798 0.05021 0.04545 -0.1185 0.8924 0.1389
-3.250 0.1193 0.04694 0.04214 -0.1225 0.8894 0.1570
-3.000 0.1527 0.04447 0.03948 -0.1272 0.8810 0.1837
-2.750 0.1934 0.04155 0.03650 -0.1310 0.8771 0.2074
-2.500 0.3108 0.02976 0.02270 -0.1510 0.8777 0.0724
-2.250 0.3661 0.02678 0.01873 -0.1553 0.8754 0.0646
-2.000 0.3994 0.02496 0.01663 -0.1565 0.8688 0.0660
-1.750 0.4371 0.02374 0.01525 -0.1582 0.8635 0.0746
-1.500 0.4801 0.02211 0.01352 -0.1604 0.8603 0.0855
-1.250 0.5070 0.02134 0.01288 -0.1603 0.8522 0.1247
-1.000 0.5470 0.01919 0.01225 -0.1630 0.8482 0.4973
-0.750 0.5571 0.01825 0.01212 -0.1579 0.8414 1.0000
-0.500 0.5882 0.01845 0.01193 -0.1585 0.8345 1.0000
-0.250 0.6263 0.01836 0.01152 -0.1600 0.8306 1.0000
0.000 0.6483 0.01892 0.01189 -0.1593 0.8212 1.0000
0.250 0.6840 0.01889 0.01163 -0.1604 0.8168 1.0000
0.500 0.7063 0.01947 0.01209 -0.1598 0.8081 1.0000
0.750 0.7399 0.01951 0.01196 -0.1606 0.8032 1.0000
1.000 0.7632 0.02006 0.01243 -0.1602 0.7951 1.0000
1.250 0.7945 0.02021 0.01246 -0.1606 0.7896 1.0000
1.500 0.8198 0.02067 0.01286 -0.1604 0.7825 1.0000
1.750 0.8481 0.02097 0.01310 -0.1605 0.7760 1.0000
2.000 0.8784 0.02116 0.01324 -0.1607 0.7707 1.0000
2.250 0.9008 0.02178 0.01384 -0.1601 0.7624 1.0000
2.500 0.9347 0.02175 0.01376 -0.1607 0.7582 1.0000
2.750 0.9531 0.02262 0.01466 -0.1597 0.7486 1.0000
3.000 0.9866 0.02256 0.01461 -0.1602 0.7441 1.0000
3.250 1.0053 0.02342 0.01551 -0.1592 0.7345 1.0000
3.500 1.0391 0.02330 0.01538 -0.1596 0.7296 1.0000
3.750 1.0581 0.02410 0.01626 -0.1585 0.7198 1.0000
4.000 1.0928 0.02385 0.01606 -0.1589 0.7147 1.0000
4.250 1.1119 0.02460 0.01690 -0.1578 0.7044 1.0000
4.500 1.1424 0.02458 0.01693 -0.1577 0.6976 1.0000
4.750 1.1673 0.02487 0.01731 -0.1570 0.6883 1.0000
5.000 1.1911 0.02522 0.01780 -0.1561 0.6786 1.0000
5.250 1.2258 0.02473 0.01736 -0.1562 0.6713 1.0000
5.500 1.2479 0.02507 0.01783 -0.1550 0.6597 1.0000
5.750 1.2734 0.02514 0.01805 -0.1541 0.6489 1.0000
6.000 1.3041 0.02480 0.01780 -0.1537 0.6390 1.0000
6.250 1.3342 0.02440 0.01750 -0.1531 0.6276 1.0000
6.500 1.3595 0.02423 0.01748 -0.1519 0.6139 1.0000
6.750 1.3859 0.02392 0.01733 -0.1508 0.5994 1.0000
7.000 1.4129 0.02351 0.01703 -0.1497 0.5839 1.0000
7.250 1.4340 0.02336 0.01708 -0.1478 0.5652 1.0000
7.500 1.4571 0.02291 0.01676 -0.1460 0.5434 1.0000
7.750 1.4767 0.02228 0.01619 -0.1433 0.5119 1.0000
8.000 1.4886 0.02214 0.01606 -0.1398 0.4683 1.0000
8.250 1.4957 0.02256 0.01634 -0.1359 0.4108 1.0000
8.500 1.4975 0.02368 0.01709 -0.1316 0.3415 1.0000
8.750 1.4931 0.02546 0.01844 -0.1269 0.2756 1.0000
9.000 1.4820 0.02761 0.02019 -0.1215 0.2176 1.0000
9.250 1.4661 0.03032 0.02246 -0.1162 0.1603 1.0000
9.500 1.4464 0.03379 0.02543 -0.1112 0.1083 1.0000
9.750 1.4287 0.03756 0.02884 -0.1071 0.0789 1.0000
10.000 1.4194 0.04091 0.03212 -0.1040 0.0645 1.0000
10.250 1.4126 0.04418 0.03538 -0.1015 0.0577 1.0000
10.500 1.4148 0.04685 0.03818 -0.0994 0.0525 1.0000
10.750 1.4190 0.04947 0.04080 -0.0976 0.0487 1.0000
11.000 1.4354 0.05187 0.04315 -0.0956 0.0455 1.0000
11.250 1.4561 0.05389 0.04536 -0.0941 0.0426 1.0000
11.500 1.4728 0.05615 0.04776 -0.0930 0.0397 1.0000
11.750 1.5075 0.05895 0.05060 -0.0925 0.0374 1.0000
12.000 1.5550 0.06474 0.05677 -0.0935 0.0365 1.0000
12.250 1.5629 0.06920 0.06160 -0.0921 0.0364 1.0000
12.500 1.5612 0.07309 0.06587 -0.0901 0.0366 1.0000
12.750 1.5540 0.07671 0.06984 -0.0881 0.0368 1.0000
13.000 1.5425 0.08054 0.07402 -0.0864 0.0370 1.0000
13.250 1.5272 0.08463 0.07847 -0.0850 0.0374 1.0000
13.500 1.5080 0.08947 0.08370 -0.0843 0.0379 1.0000
13.750 1.4835 0.09522 0.08985 -0.0845 0.0385 1.0000
14.000 1.4535 0.10187 0.09687 -0.0859 0.0390 1.0000
14.250 1.4243 0.10917 0.10451 -0.0885 0.0396 1.0000
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Polar data table (+)
Polar graphs
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