E207 (12.04%) (e207-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: E207 (12.04%) (e207-il) Reynolds number: 100,000 Max Cl/Cd: 52.34 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e207-il-100000.txt Download as CSV file: xf-e207-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: E207 (12.04%)
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4042 0.09699 0.09217 -0.0287 1.0000 0.1320
-9.000 -0.4365 0.09383 0.08919 -0.0350 1.0000 0.1378
-8.750 -0.4240 0.08946 0.08483 -0.0334 1.0000 0.1405
-8.500 -0.4099 0.08654 0.08192 -0.0317 1.0000 0.1447
-8.250 -0.4363 0.08325 0.07878 -0.0355 1.0000 0.1514
-8.000 -0.4647 0.07882 0.07450 -0.0383 1.0000 0.1540
-7.750 -0.4369 0.07648 0.07215 -0.0339 1.0000 0.1578
-7.500 -0.4482 0.07325 0.06902 -0.0344 1.0000 0.1626
-6.750 -0.5393 0.04617 0.04081 -0.0402 1.0000 0.0785
-6.500 -0.5494 0.04120 0.03491 -0.0361 1.0000 0.0685
-6.250 -0.5462 0.03815 0.03170 -0.0336 1.0000 0.0673
-6.000 -0.5420 0.03566 0.02895 -0.0310 1.0000 0.0663
-5.750 -0.5300 0.03313 0.02604 -0.0297 0.9986 0.0656
-5.500 -0.4864 0.03031 0.02250 -0.0333 0.9893 0.0680
-5.250 -0.4421 0.02780 0.01941 -0.0366 0.9804 0.0693
-5.000 -0.3986 0.02506 0.01655 -0.0399 0.9720 0.0724
-4.750 -0.3559 0.02349 0.01484 -0.0427 0.9614 0.0785
-4.500 -0.3131 0.02194 0.01329 -0.0457 0.9515 0.0895
-4.250 -0.2688 0.02027 0.01168 -0.0486 0.9429 0.1108
-4.000 -0.2346 0.01847 0.01042 -0.0503 0.9311 0.1844
-3.750 -0.2013 0.01689 0.00974 -0.0521 0.9199 0.3341
-3.500 -0.1677 0.01616 0.00962 -0.0529 0.9093 0.4955
-3.250 -0.1316 0.01579 0.00941 -0.0536 0.8995 0.5824
-3.000 -0.1016 0.01557 0.00927 -0.0531 0.8870 0.6434
-2.750 -0.0723 0.01538 0.00914 -0.0523 0.8752 0.6963
-2.500 -0.0425 0.01522 0.00900 -0.0515 0.8642 0.7452
-2.250 -0.0105 0.01506 0.00883 -0.0509 0.8546 0.7906
-2.000 0.0186 0.01506 0.00880 -0.0498 0.8424 0.8321
-1.750 0.0550 0.01513 0.00880 -0.0501 0.8315 0.8717
-1.500 0.1045 0.01523 0.00873 -0.0530 0.8223 0.9060
-1.250 0.1621 0.01534 0.00863 -0.0579 0.8119 0.9336
-1.000 0.2255 0.01539 0.00848 -0.0646 0.8010 0.9581
-0.750 0.2912 0.01528 0.00815 -0.0722 0.7905 0.9809
-0.500 0.3535 0.01501 0.00767 -0.0796 0.7803 1.0000
-0.250 0.3665 0.01502 0.00759 -0.0780 0.7683 1.0000
0.000 0.3813 0.01512 0.00760 -0.0765 0.7575 1.0000
0.250 0.3991 0.01525 0.00760 -0.0750 0.7484 1.0000
0.500 0.4173 0.01545 0.00771 -0.0737 0.7385 1.0000
0.750 0.4361 0.01571 0.00790 -0.0724 0.7289 1.0000
1.000 0.4582 0.01589 0.00796 -0.0713 0.7212 1.0000
1.250 0.4774 0.01624 0.00828 -0.0701 0.7114 1.0000
1.500 0.4996 0.01650 0.00848 -0.0691 0.7037 1.0000
1.750 0.5207 0.01683 0.00877 -0.0680 0.6948 1.0000
2.000 0.5424 0.01718 0.00909 -0.0670 0.6868 1.0000
2.250 0.5652 0.01748 0.00934 -0.0661 0.6789 1.0000
2.500 0.5864 0.01790 0.00978 -0.0650 0.6705 1.0000
2.750 0.6102 0.01818 0.01002 -0.0642 0.6633 1.0000
3.000 0.6308 0.01866 0.01053 -0.0631 0.6547 1.0000
3.250 0.6557 0.01892 0.01075 -0.0624 0.6479 1.0000
3.500 0.6756 0.01944 0.01136 -0.0613 0.6388 1.0000
3.750 0.7019 0.01966 0.01153 -0.0606 0.6323 1.0000
4.000 0.7213 0.02021 0.01217 -0.0594 0.6225 1.0000
4.250 0.7457 0.02051 0.01251 -0.0586 0.6150 1.0000
4.500 0.7681 0.02089 0.01294 -0.0576 0.6058 1.0000
4.750 0.7899 0.02131 0.01343 -0.0566 0.5966 1.0000
5.000 0.8170 0.02141 0.01351 -0.0559 0.5886 1.0000
5.250 0.8372 0.02186 0.01410 -0.0547 0.5778 1.0000
5.500 0.8607 0.02211 0.01442 -0.0537 0.5679 1.0000
5.750 0.8888 0.02205 0.01434 -0.0531 0.5587 1.0000
6.000 0.9098 0.02234 0.01475 -0.0517 0.5466 1.0000
6.250 0.9324 0.02251 0.01504 -0.0506 0.5347 1.0000
6.500 0.9565 0.02255 0.01515 -0.0495 0.5228 1.0000
6.750 0.9814 0.02246 0.01512 -0.0484 0.5101 1.0000
7.000 1.0059 0.02234 0.01505 -0.0473 0.4964 1.0000
7.250 1.0290 0.02220 0.01502 -0.0459 0.4811 1.0000
7.500 1.0512 0.02204 0.01496 -0.0444 0.4643 1.0000
7.750 1.0732 0.02182 0.01480 -0.0429 0.4460 1.0000
8.000 1.0951 0.02156 0.01457 -0.0412 0.4259 1.0000
8.250 1.1118 0.02150 0.01464 -0.0390 0.4013 1.0000
8.500 1.1269 0.02153 0.01475 -0.0365 0.3724 1.0000
8.750 1.1385 0.02179 0.01500 -0.0336 0.3362 1.0000
9.000 1.1453 0.02245 0.01552 -0.0303 0.2929 1.0000
9.250 1.1469 0.02362 0.01642 -0.0265 0.2488 1.0000
9.500 1.1447 0.02518 0.01763 -0.0226 0.2131 1.0000
9.750 1.1410 0.02682 0.01904 -0.0185 0.1847 1.0000
10.000 1.1373 0.02849 0.02059 -0.0147 0.1610 1.0000
10.250 1.1347 0.03033 0.02225 -0.0114 0.1418 1.0000
10.500 1.1330 0.03217 0.02408 -0.0087 0.1243 1.0000
10.750 1.1313 0.03416 0.02601 -0.0064 0.1091 1.0000
11.000 1.1296 0.03629 0.02810 -0.0044 0.0956 1.0000
11.250 1.1296 0.03855 0.03033 -0.0028 0.0837 1.0000
11.500 1.1313 0.04093 0.03269 -0.0013 0.0731 1.0000
11.750 1.1375 0.04337 0.03505 0.0002 0.0638 1.0000
12.000 1.1441 0.04560 0.03733 0.0013 0.0573 1.0000
12.250 1.1526 0.04818 0.04001 0.0025 0.0513 1.0000
12.500 1.1614 0.05058 0.04255 0.0035 0.0475 1.0000
12.750 1.1901 0.05393 0.04583 0.0043 0.0438 1.0000
13.000 1.1887 0.05703 0.04932 0.0054 0.0428 1.0000
13.250 1.1871 0.06040 0.05300 0.0061 0.0422 1.0000
13.500 1.1791 0.06420 0.05712 0.0065 0.0415 1.0000
13.750 1.1678 0.06823 0.06145 0.0065 0.0407 1.0000
14.000 1.1549 0.07272 0.06620 0.0059 0.0404 1.0000
14.250 1.1393 0.07762 0.07137 0.0048 0.0403 1.0000
14.500 1.1206 0.08313 0.07714 0.0031 0.0403 1.0000
14.750 1.0992 0.08935 0.08360 0.0006 0.0406 1.0000
15.000 1.0759 0.09613 0.09060 -0.0027 0.0409 1.0000
15.250 1.0514 0.10373 0.09841 -0.0067 0.0415 1.0000
15.500 1.0282 0.11180 0.10664 -0.0112 0.0424 1.0000
15.750 1.0040 0.12065 0.11558 -0.0165 0.0430 1.0000
16.000 0.9799 0.13033 0.12537 -0.0223 0.0435 1.0000
16.250 0.8873 0.16535 0.16043 -0.0440 0.0532 1.0000
16.500 0.8880 0.17126 0.16632 -0.0463 0.0541 1.0000
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Polar data table (+)
Polar graphs
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