E475 (15.01%) (e475-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: E475 (15.01%) (e475-il) Reynolds number: 200,000 Max Cl/Cd: 51.35 at α=9° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e475-il-200000-n5.txt Download as CSV file: xf-e475-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E475 (15.01%)
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
------ -------- --------- --------- -------- -------- --------
-17.500 -1.0288 0.09186 0.08674 -0.0345 1.0000 0.0611
-17.250 -1.0490 0.08527 0.08003 -0.0378 1.0000 0.0626
-17.000 -1.0690 0.07889 0.07349 -0.0409 1.0000 0.0641
-16.750 -1.0914 0.07238 0.06691 -0.0441 1.0000 0.0654
-16.500 -1.1138 0.06599 0.06042 -0.0472 1.0000 0.0666
-16.250 -1.1341 0.05999 0.05431 -0.0502 1.0000 0.0681
-16.000 -1.1502 0.05474 0.04893 -0.0526 1.0000 0.0697
-15.750 -1.1628 0.05015 0.04419 -0.0545 1.0000 0.0719
-15.500 -1.1718 0.04624 0.04014 -0.0559 1.0000 0.0740
-15.250 -1.1826 0.04246 0.03627 -0.0569 1.0000 0.0759
-15.000 -1.1893 0.03942 0.03315 -0.0572 1.0000 0.0783
-14.750 -1.1922 0.03701 0.03062 -0.0569 1.0000 0.0811
-14.500 -1.1915 0.03506 0.02854 -0.0561 1.0000 0.0839
-14.250 -1.1944 0.03310 0.02654 -0.0549 1.0000 0.0867
-14.000 -1.1935 0.03156 0.02493 -0.0533 1.0000 0.0899
-13.750 -1.1891 0.03032 0.02357 -0.0516 1.0000 0.0934
-13.500 -1.1859 0.02914 0.02232 -0.0495 1.0000 0.0967
-13.250 -1.1823 0.02810 0.02124 -0.0472 1.0000 0.1003
-13.000 -1.1754 0.02725 0.02030 -0.0449 1.0000 0.1045
-12.750 -1.1693 0.02645 0.01944 -0.0424 1.0000 0.1082
-12.500 -1.1646 0.02574 0.01871 -0.0394 1.0000 0.1120
-12.250 -1.1575 0.02515 0.01804 -0.0366 1.0000 0.1161
-12.000 -1.1502 0.02460 0.01740 -0.0335 1.0000 0.1198
-11.750 -1.1470 0.02409 0.01688 -0.0297 1.0000 0.1228
-11.500 -1.1429 0.02368 0.01643 -0.0259 1.0000 0.1262
-11.250 -1.1361 0.02329 0.01595 -0.0223 1.0000 0.1298
-11.000 -1.1272 0.02285 0.01545 -0.0192 1.0000 0.1333
-10.750 -1.1189 0.02243 0.01502 -0.0159 1.0000 0.1364
-10.500 -1.1082 0.02206 0.01460 -0.0130 1.0000 0.1400
-10.250 -1.0954 0.02169 0.01412 -0.0104 1.0000 0.1439
-10.000 -1.0828 0.02130 0.01368 -0.0078 1.0000 0.1473
-9.750 -1.0702 0.02095 0.01333 -0.0051 1.0000 0.1508
-9.500 -1.0557 0.02062 0.01295 -0.0028 1.0000 0.1546
-9.250 -1.0397 0.02031 0.01251 -0.0006 1.0000 0.1586
-9.000 -1.0245 0.01996 0.01215 0.0016 1.0000 0.1621
-8.750 -1.0087 0.01965 0.01183 0.0037 1.0000 0.1656
-8.500 -0.9916 0.01936 0.01149 0.0057 1.0000 0.1694
-8.250 -0.9736 0.01910 0.01111 0.0075 1.0000 0.1735
-8.000 -0.9563 0.01878 0.01079 0.0094 1.0000 0.1769
-7.750 -0.9385 0.01851 0.01052 0.0112 1.0000 0.1805
-7.500 -0.9198 0.01827 0.01023 0.0129 1.0000 0.1845
-7.250 -0.9004 0.01804 0.00991 0.0145 1.0000 0.1884
-7.000 -0.8816 0.01776 0.00963 0.0162 1.0000 0.1917
-6.750 -0.8627 0.01752 0.00939 0.0178 1.0000 0.1953
-6.500 -0.8316 0.01732 0.00916 0.0170 0.9976 0.2000
-6.250 -0.7969 0.01716 0.00891 0.0155 0.9945 0.2045
-6.000 -0.7631 0.01690 0.00870 0.0141 0.9911 0.2088
-5.750 -0.7279 0.01669 0.00849 0.0126 0.9867 0.2136
-5.500 -0.6874 0.01652 0.00826 0.0099 0.9824 0.2188
-5.250 -0.6496 0.01625 0.00800 0.0079 0.9763 0.2233
-5.000 -0.6057 0.01597 0.00776 0.0047 0.9700 0.2289
-4.750 -0.5658 0.01571 0.00747 0.0024 0.9621 0.2343
-4.500 -0.5208 0.01539 0.00716 -0.0010 0.9554 0.2394
-4.250 -0.4865 0.01508 0.00690 -0.0021 0.9473 0.2446
-4.000 -0.4466 0.01480 0.00663 -0.0044 0.9410 0.2510
-3.750 -0.4130 0.01452 0.00637 -0.0053 0.9336 0.2561
-3.500 -0.3801 0.01421 0.00613 -0.0061 0.9253 0.2618
-3.250 -0.3520 0.01397 0.00589 -0.0059 0.9144 0.2680
-3.000 -0.3214 0.01368 0.00565 -0.0061 0.9035 0.2741
-2.750 -0.2969 0.01343 0.00544 -0.0052 0.8874 0.2802
-2.500 -0.2726 0.01321 0.00522 -0.0041 0.8656 0.2868
-2.250 -0.2377 0.01286 0.00492 -0.0051 0.8369 0.2950
-1.750 -0.1551 0.01232 0.00411 -0.0093 0.7253 0.3160
-1.500 -0.1304 0.01239 0.00393 -0.0082 0.6608 0.3259
-1.250 -0.1086 0.01251 0.00384 -0.0067 0.6040 0.3375
-1.000 -0.0875 0.01259 0.00378 -0.0052 0.5555 0.3502
-0.750 -0.0659 0.01266 0.00374 -0.0038 0.5153 0.3647
-0.500 -0.0441 0.01272 0.00371 -0.0025 0.4802 0.3807
-0.250 -0.0220 0.01276 0.00369 -0.0012 0.4489 0.3995
0.000 0.0000 0.01278 0.00369 0.0000 0.4222 0.4222
0.250 0.0220 0.01276 0.00369 0.0012 0.3994 0.4489
0.500 0.0441 0.01272 0.00371 0.0025 0.3807 0.4801
0.750 0.0659 0.01267 0.00374 0.0038 0.3646 0.5153
1.000 0.0875 0.01260 0.00378 0.0052 0.3502 0.5555
1.250 0.1086 0.01251 0.00384 0.0067 0.3374 0.6039
1.500 0.1304 0.01239 0.00393 0.0082 0.3259 0.6610
1.750 0.1551 0.01232 0.00411 0.0093 0.3161 0.7255
2.000 0.1901 0.01248 0.00446 0.0084 0.3059 0.7905
2.250 0.2377 0.01286 0.00492 0.0051 0.2950 0.8370
2.500 0.2725 0.01321 0.00522 0.0041 0.2868 0.8658
2.750 0.2969 0.01343 0.00544 0.0052 0.2802 0.8873
3.000 0.3216 0.01368 0.00565 0.0061 0.2740 0.9033
3.250 0.3520 0.01397 0.00589 0.0059 0.2680 0.9146
3.500 0.3798 0.01421 0.00612 0.0062 0.2617 0.9252
3.750 0.4129 0.01452 0.00637 0.0053 0.2561 0.9337
4.000 0.4465 0.01480 0.00662 0.0044 0.2509 0.9410
4.250 0.4864 0.01507 0.00691 0.0021 0.2448 0.9473
4.500 0.5208 0.01539 0.00716 0.0009 0.2394 0.9555
4.750 0.5659 0.01571 0.00747 -0.0024 0.2343 0.9621
5.000 0.6057 0.01597 0.00776 -0.0047 0.2288 0.9700
5.250 0.6497 0.01624 0.00800 -0.0079 0.2233 0.9764
5.500 0.6875 0.01652 0.00826 -0.0100 0.2188 0.9824
5.750 0.7280 0.01669 0.00848 -0.0126 0.2136 0.9867
6.000 0.7631 0.01690 0.00869 -0.0142 0.2088 0.9911
6.250 0.7970 0.01716 0.00890 -0.0156 0.2046 0.9945
6.500 0.8317 0.01732 0.00915 -0.0170 0.1999 0.9977
6.750 0.8625 0.01751 0.00938 -0.0178 0.1952 1.0000
7.000 0.8815 0.01776 0.00962 -0.0161 0.1916 1.0000
7.250 0.9003 0.01804 0.00990 -0.0145 0.1884 1.0000
7.500 0.9197 0.01826 0.01022 -0.0129 0.1843 1.0000
7.750 0.9384 0.01850 0.01051 -0.0112 0.1805 1.0000
8.000 0.9562 0.01877 0.01078 -0.0094 0.1769 1.0000
8.250 0.9735 0.01910 0.01111 -0.0075 0.1736 1.0000
8.500 0.9916 0.01936 0.01149 -0.0057 0.1696 1.0000
8.750 1.0087 0.01965 0.01183 -0.0037 0.1657 1.0000
9.000 1.0244 0.01995 0.01214 -0.0016 0.1621 1.0000
9.250 1.0397 0.02031 0.01251 0.0006 0.1586 1.0000
9.500 1.0557 0.02062 0.01294 0.0028 0.1547 1.0000
9.750 1.0701 0.02094 0.01332 0.0051 0.1508 1.0000
10.000 1.0828 0.02130 0.01368 0.0078 0.1473 1.0000
10.250 1.0954 0.02169 0.01412 0.0104 0.1440 1.0000
10.500 1.1083 0.02205 0.01460 0.0130 0.1401 1.0000
10.750 1.1190 0.02243 0.01502 0.0159 0.1364 1.0000
11.000 1.1272 0.02285 0.01544 0.0192 0.1332 1.0000
11.250 1.1363 0.02328 0.01594 0.0223 0.1299 1.0000
11.500 1.1431 0.02368 0.01643 0.0258 0.1262 1.0000
11.750 1.1473 0.02409 0.01688 0.0297 0.1228 1.0000
12.000 1.1504 0.02460 0.01739 0.0335 0.1197 1.0000
12.250 1.1579 0.02514 0.01803 0.0365 0.1160 1.0000
12.500 1.1650 0.02573 0.01871 0.0394 0.1120 1.0000
12.750 1.1698 0.02645 0.01943 0.0423 0.1081 1.0000
13.000 1.1761 0.02724 0.02029 0.0448 0.1044 1.0000
13.250 1.1829 0.02809 0.02123 0.0471 0.1002 1.0000
13.500 1.1866 0.02913 0.02230 0.0494 0.0965 1.0000
13.750 1.1901 0.03030 0.02355 0.0514 0.0933 1.0000
14.000 1.1944 0.03155 0.02491 0.0532 0.0898 1.0000
14.250 1.1953 0.03309 0.02653 0.0547 0.0866 1.0000
14.500 1.1927 0.03503 0.02851 0.0560 0.0840 1.0000
14.750 1.1934 0.03697 0.03059 0.0567 0.0810 1.0000
15.000 1.1905 0.03940 0.03312 0.0570 0.0781 1.0000
15.250 1.1836 0.04246 0.03627 0.0567 0.0757 1.0000
15.500 1.1728 0.04624 0.04013 0.0557 0.0738 1.0000
15.750 1.1645 0.05008 0.04412 0.0544 0.0716 1.0000
16.000 1.1523 0.05463 0.04882 0.0524 0.0697 1.0000
16.250 1.1361 0.05989 0.05421 0.0500 0.0680 1.0000
16.500 1.1160 0.06586 0.06029 0.0471 0.0666 1.0000
16.750 1.0931 0.07233 0.06686 0.0439 0.0653 1.0000
17.000 1.0717 0.07870 0.07330 0.0408 0.0641 1.0000
17.250 1.0509 0.08521 0.07996 0.0375 0.0625 1.0000
17.500 1.0305 0.09185 0.08672 0.0342 0.0609 1.0000
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Polar data table (+)
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