E231 (e231-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: E231 (e231-il) Reynolds number: 200,000 Max Cl/Cd: 77.95 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e231-il-200000.txt Download as CSV file: xf-e231-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: E231
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
------ -------- --------- --------- -------- -------- --------
-12.000 -0.2803 0.12195 0.11880 -0.0419 1.0000 0.0350
-11.750 -0.2930 0.12146 0.11836 -0.0389 1.0000 0.0355
-11.500 -0.3033 0.12031 0.11725 -0.0368 1.0000 0.0360
-11.250 -0.2998 0.11635 0.11330 -0.0392 0.9984 0.0373
-11.000 -0.2982 0.11191 0.10886 -0.0425 0.9966 0.0388
-10.750 -0.2997 0.10719 0.10415 -0.0470 0.9947 0.0400
-10.500 -0.3028 0.10224 0.09921 -0.0518 0.9925 0.0405
-10.250 -0.3041 0.09712 0.09410 -0.0562 0.9899 0.0407
-10.000 -0.3038 0.09168 0.08866 -0.0605 0.9876 0.0408
-9.750 -0.2981 0.08564 0.08266 -0.0601 0.9861 0.0421
-9.500 -0.2842 0.08211 0.07909 -0.0607 0.9845 0.0435
-9.250 -0.2763 0.07775 0.07474 -0.0633 0.9827 0.0449
-9.000 -0.2767 0.07299 0.06998 -0.0660 0.9789 0.0462
-8.750 -0.2785 0.06735 0.06435 -0.0704 0.9757 0.0473
-8.500 -0.2861 0.06022 0.05723 -0.0777 0.9728 0.0478
-8.250 -0.4021 0.06546 0.06209 -0.0792 0.9707 0.0428
-8.000 -0.3989 0.06271 0.05929 -0.0790 0.9643 0.0436
-7.750 -0.3887 0.05939 0.05588 -0.0805 0.9602 0.0453
-7.500 -0.3753 0.05536 0.05164 -0.0831 0.9572 0.0479
-7.250 -0.3838 0.05483 0.05053 -0.0794 0.9475 0.0525
-5.750 -0.3228 0.03196 0.02571 -0.0673 0.9193 0.0286
-5.500 -0.2987 0.02817 0.02109 -0.0652 0.9166 0.0223
-5.250 -0.2676 0.02597 0.01865 -0.0658 0.9149 0.0213
-5.000 -0.2603 0.02482 0.01728 -0.0618 0.9078 0.0212
-4.750 -0.2317 0.02318 0.01544 -0.0617 0.9050 0.0212
-4.500 -0.1992 0.02172 0.01379 -0.0623 0.9029 0.0223
-4.250 -0.1692 0.02050 0.01261 -0.0629 0.9011 0.0275
-4.000 -0.1614 0.02031 0.01235 -0.0591 0.8939 0.0298
-3.750 -0.1405 0.01912 0.01117 -0.0577 0.8902 0.0336
-3.500 -0.1146 0.01816 0.01021 -0.0571 0.8878 0.0542
-3.250 -0.1176 0.01707 0.00987 -0.0517 0.8800 0.1805
-3.000 -0.1169 0.01541 0.00963 -0.0471 0.8752 0.4970
-2.750 -0.0869 0.01494 0.01043 -0.0452 0.8739 0.8260
-2.500 -0.0548 0.01562 0.01100 -0.0440 0.8724 0.8842
-2.250 0.0108 0.01640 0.01155 -0.0497 0.8725 0.9080
-2.000 0.0937 0.01685 0.01178 -0.0596 0.8735 0.9229
-1.750 0.1604 0.01699 0.01174 -0.0668 0.8733 0.9344
-1.500 0.2107 0.01702 0.01164 -0.0711 0.8717 0.9450
-1.250 0.2500 0.01719 0.01174 -0.0737 0.8666 0.9567
-1.000 0.3066 0.01690 0.01134 -0.0796 0.8644 0.9633
-0.750 0.3483 0.01667 0.01104 -0.0824 0.8612 0.9716
-0.500 0.3962 0.01627 0.01056 -0.0865 0.8588 0.9781
-0.250 0.4345 0.01612 0.01038 -0.0892 0.8527 0.9856
0.000 0.4756 0.01574 0.00997 -0.0922 0.8481 0.9919
0.250 0.5169 0.01525 0.00943 -0.0949 0.8445 0.9971
0.500 0.5453 0.01514 0.00932 -0.0956 0.8368 1.0000
0.750 0.5666 0.01494 0.00908 -0.0943 0.8312 1.0000
1.000 0.5849 0.01496 0.00911 -0.0928 0.8232 1.0000
1.250 0.6066 0.01474 0.00887 -0.0914 0.8172 1.0000
1.500 0.6255 0.01472 0.00887 -0.0899 0.8091 1.0000
1.750 0.6478 0.01447 0.00860 -0.0886 0.8030 1.0000
2.000 0.6672 0.01442 0.00858 -0.0871 0.7945 1.0000
2.250 0.6903 0.01413 0.00827 -0.0859 0.7883 1.0000
2.500 0.7098 0.01406 0.00826 -0.0844 0.7790 1.0000
2.750 0.7343 0.01370 0.00788 -0.0833 0.7730 1.0000
3.000 0.7536 0.01359 0.00783 -0.0817 0.7623 1.0000
3.250 0.7748 0.01340 0.00766 -0.0803 0.7527 1.0000
3.500 0.7990 0.01307 0.00734 -0.0792 0.7448 1.0000
3.750 0.8190 0.01292 0.00725 -0.0776 0.7328 1.0000
4.000 0.8397 0.01274 0.00712 -0.0761 0.7203 1.0000
4.250 0.8606 0.01256 0.00700 -0.0746 0.7068 1.0000
4.500 0.8815 0.01239 0.00686 -0.0730 0.6915 1.0000
4.750 0.9024 0.01225 0.00673 -0.0715 0.6742 1.0000
5.000 0.9212 0.01220 0.00670 -0.0696 0.6514 1.0000
5.250 0.9398 0.01219 0.00667 -0.0677 0.6257 1.0000
5.500 0.9572 0.01228 0.00671 -0.0656 0.5949 1.0000
5.750 0.9725 0.01249 0.00680 -0.0631 0.5589 1.0000
6.000 0.9850 0.01284 0.00698 -0.0602 0.5193 1.0000
6.250 0.9942 0.01331 0.00727 -0.0568 0.4777 1.0000
6.500 1.0012 0.01385 0.00764 -0.0530 0.4389 1.0000
6.750 1.0054 0.01442 0.00805 -0.0488 0.4033 1.0000
7.000 1.0082 0.01498 0.00850 -0.0444 0.3713 1.0000
7.250 1.0088 0.01553 0.00893 -0.0396 0.3427 1.0000
7.500 1.0069 0.01606 0.00936 -0.0343 0.3176 1.0000
7.750 1.0028 0.01655 0.00975 -0.0287 0.2948 1.0000
8.000 0.9963 0.01700 0.01012 -0.0225 0.2753 1.0000
8.250 0.9944 0.01754 0.01058 -0.0175 0.2537 1.0000
8.500 0.9963 0.01823 0.01117 -0.0135 0.2324 1.0000
8.750 1.0017 0.01897 0.01185 -0.0103 0.2111 1.0000
9.000 1.0077 0.01981 0.01260 -0.0073 0.1908 1.0000
9.250 1.0158 0.02066 0.01343 -0.0048 0.1716 1.0000
9.500 1.0229 0.02164 0.01433 -0.0024 0.1539 1.0000
9.750 1.0299 0.02270 0.01530 0.0000 0.1381 1.0000
10.000 1.0389 0.02371 0.01631 0.0020 0.1232 1.0000
10.250 1.0472 0.02482 0.01739 0.0041 0.1101 1.0000
10.500 1.0543 0.02606 0.01859 0.0061 0.0984 1.0000
10.750 1.0638 0.02716 0.01975 0.0078 0.0875 1.0000
11.000 1.0725 0.02835 0.02100 0.0095 0.0774 1.0000
11.250 1.0795 0.02973 0.02240 0.0113 0.0686 1.0000
11.500 1.0840 0.03132 0.02397 0.0130 0.0607 1.0000
11.750 1.0929 0.03258 0.02537 0.0144 0.0534 1.0000
12.000 1.0965 0.03441 0.02726 0.0162 0.0469 1.0000
12.250 1.1008 0.03609 0.02897 0.0176 0.0409 1.0000
12.500 1.1040 0.03808 0.03107 0.0192 0.0354 1.0000
12.750 1.1039 0.04027 0.03326 0.0206 0.0305 1.0000
13.000 1.1062 0.04246 0.03563 0.0219 0.0262 1.0000
13.250 1.1091 0.04451 0.03775 0.0228 0.0239 1.0000
13.500 1.1053 0.04759 0.04089 0.0241 0.0210 1.0000
13.750 1.1073 0.04989 0.04339 0.0247 0.0189 1.0000
14.000 1.1071 0.05246 0.04604 0.0251 0.0171 1.0000
14.250 1.0988 0.05623 0.04987 0.0256 0.0150 1.0000
14.500 1.0994 0.05919 0.05303 0.0261 0.0147 1.0000
14.750 1.0964 0.06262 0.05672 0.0261 0.0138 1.0000
15.000 1.0924 0.06630 0.06060 0.0259 0.0133 1.0000
15.250 1.0870 0.07030 0.06481 0.0254 0.0130 1.0000
15.500 1.0789 0.07486 0.06958 0.0246 0.0129 1.0000
15.750 1.0700 0.07953 0.07441 0.0230 0.0122 1.0000
16.000 1.0581 0.08505 0.08016 0.0212 0.0123 1.0000
16.250 1.0453 0.09092 0.08625 0.0188 0.0123 1.0000
16.500 1.0312 0.09729 0.09281 0.0157 0.0121 1.0000
16.750 1.0137 0.10465 0.10039 0.0120 0.0122 1.0000
17.000 0.9968 0.11227 0.10820 0.0077 0.0122 1.0000
17.250 0.9752 0.12138 0.11753 0.0024 0.0125 1.0000
17.500 0.9489 0.13222 0.12858 -0.0041 0.0131 1.0000
17.750 0.9231 0.14372 0.14021 -0.0111 0.0133 1.0000
18.000 0.8993 0.15524 0.15183 -0.0178 0.0144 1.0000
18.250 0.8714 0.16890 0.16552 -0.0251 0.0150 1.0000
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