E186 (10.27%) (e186-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: E186 (10.27%) (e186-il) Reynolds number: 1,000,000 Max Cl/Cd: 73.38 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e186-il-1000000-n5.txt Download as CSV file: xf-e186-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E186 (10.27%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -1.0779 0.04747 0.04560 -0.0025 1.0000 0.0044
-12.250 -1.1008 0.04339 0.04134 -0.0013 1.0000 0.0045
-12.000 -1.1335 0.03907 0.03674 0.0030 1.0000 0.0045
-11.750 -1.1390 0.03702 0.03453 0.0064 1.0000 0.0045
-11.500 -1.1363 0.03494 0.03227 0.0086 1.0000 0.0047
-11.250 -1.1302 0.03293 0.03008 0.0106 1.0000 0.0048
-11.000 -1.1222 0.03089 0.02784 0.0126 1.0000 0.0050
-10.750 -1.1110 0.02908 0.02581 0.0143 1.0000 0.0051
-10.500 -1.0968 0.02748 0.02401 0.0157 0.9703 0.0053
-10.250 -1.0869 0.02650 0.02271 0.0187 0.8764 0.0055
-10.000 -1.0687 0.02586 0.02184 0.0201 0.8369 0.0057
-9.750 -1.0506 0.02484 0.02059 0.0214 0.8072 0.0058
-9.500 -1.0294 0.02422 0.01979 0.0222 0.7830 0.0059
-9.250 -1.0083 0.02347 0.01886 0.0231 0.7618 0.0059
-9.000 -0.9931 0.02150 0.01657 0.0248 0.7444 0.0062
-8.750 -0.9741 0.02019 0.01506 0.0260 0.7280 0.0064
-8.500 -0.9514 0.01952 0.01426 0.0267 0.7135 0.0066
-8.250 -0.9280 0.01896 0.01357 0.0273 0.6998 0.0068
-8.000 -0.9041 0.01844 0.01294 0.0279 0.6874 0.0070
-7.500 -0.8556 0.01739 0.01168 0.0290 0.6659 0.0075
-7.250 -0.8309 0.01690 0.01109 0.0295 0.6563 0.0078
-7.000 -0.8063 0.01637 0.01044 0.0301 0.6472 0.0082
-6.750 -0.7820 0.01570 0.00965 0.0307 0.6390 0.0084
-6.500 -0.7575 0.01508 0.00892 0.0313 0.6314 0.0086
-6.250 -0.7328 0.01449 0.00822 0.0319 0.6237 0.0088
-6.000 -0.7079 0.01394 0.00756 0.0325 0.6170 0.0090
-5.750 -0.6826 0.01345 0.00700 0.0330 0.6104 0.0092
-5.500 -0.6573 0.01299 0.00645 0.0336 0.6041 0.0094
-5.250 -0.6318 0.01257 0.00593 0.0340 0.5979 0.0095
-5.000 -0.6056 0.01225 0.00555 0.0344 0.5921 0.0097
-4.750 -0.5791 0.01199 0.00524 0.0347 0.5866 0.0098
-4.500 -0.5541 0.01145 0.00462 0.0353 0.5810 0.0101
-4.250 -0.5293 0.01089 0.00394 0.0360 0.5759 0.0107
-4.000 -0.5033 0.01052 0.00352 0.0365 0.5710 0.0113
-3.750 -0.4766 0.01026 0.00320 0.0368 0.5656 0.0118
-3.500 -0.4498 0.01004 0.00293 0.0371 0.5608 0.0124
-3.250 -0.4228 0.00983 0.00269 0.0373 0.5561 0.0128
-3.000 -0.3957 0.00966 0.00247 0.0375 0.5512 0.0132
-2.750 -0.3684 0.00950 0.00227 0.0377 0.5466 0.0137
-2.500 -0.3410 0.00936 0.00208 0.0379 0.5418 0.0141
-2.250 -0.3136 0.00923 0.00192 0.0380 0.5370 0.0147
-2.000 -0.2861 0.00912 0.00178 0.0382 0.5325 0.0157
-1.750 -0.2587 0.00897 0.00165 0.0384 0.5278 0.0216
-1.500 -0.2326 0.00865 0.00147 0.0387 0.5232 0.0639
-1.250 -0.2063 0.00838 0.00135 0.0390 0.5189 0.1083
-1.000 -0.1803 0.00806 0.00124 0.0393 0.5143 0.1660
-0.750 -0.1543 0.00777 0.00114 0.0396 0.5096 0.2254
-0.500 -0.1284 0.00749 0.00106 0.0399 0.5053 0.2900
-0.250 -0.1029 0.00717 0.00099 0.0403 0.5007 0.3641
0.000 -0.0798 0.00665 0.00091 0.0411 0.4960 0.4916
0.250 -0.0604 0.00599 0.00083 0.0428 0.4919 0.6575
0.500 -0.0406 0.00554 0.00078 0.0446 0.4877 0.7685
0.750 -0.0173 0.00518 0.00077 0.0459 0.4828 0.8632
1.000 0.0475 0.00517 0.00092 0.0378 0.4770 0.9255
1.500 0.1307 0.00545 0.00115 0.0319 0.4653 0.9491
2.000 0.1897 0.00566 0.00131 0.0314 0.4515 0.9646
2.500 0.2520 0.00588 0.00148 0.0301 0.4352 0.9734
2.750 0.2865 0.00599 0.00156 0.0287 0.4257 0.9766
3.000 0.3175 0.00611 0.00166 0.0280 0.4158 0.9804
3.250 0.3486 0.00625 0.00176 0.0273 0.4053 0.9833
3.500 0.3851 0.00634 0.00183 0.0253 0.3928 0.9846
3.750 0.4200 0.00646 0.00190 0.0237 0.3775 0.9860
4.000 0.4534 0.00658 0.00198 0.0224 0.3609 0.9874
4.250 0.4857 0.00673 0.00209 0.0213 0.3418 0.9889
4.500 0.5166 0.00704 0.00224 0.0203 0.2994 0.9902
4.750 0.5457 0.00780 0.00257 0.0193 0.2061 0.9913
5.000 0.5750 0.00826 0.00284 0.0186 0.1616 0.9925
5.250 0.6037 0.00874 0.00314 0.0179 0.1202 0.9935
5.500 0.6331 0.00921 0.00345 0.0171 0.0838 0.9943
5.750 0.6637 0.00967 0.00377 0.0161 0.0525 0.9949
6.000 0.6937 0.01012 0.00410 0.0151 0.0300 0.9956
6.250 0.7232 0.01065 0.00451 0.0142 0.0103 0.9963
6.500 0.7530 0.01098 0.00484 0.0135 0.0067 0.9970
6.750 0.7825 0.01128 0.00519 0.0128 0.0058 0.9978
7.000 0.8119 0.01163 0.00557 0.0121 0.0050 0.9985
7.250 0.8408 0.01205 0.00603 0.0115 0.0044 0.9991
7.500 0.8693 0.01256 0.00662 0.0109 0.0040 0.9997
7.750 0.8963 0.01295 0.00705 0.0106 0.0039 1.0000
8.000 0.9198 0.01341 0.00756 0.0111 0.0038 1.0000
8.250 0.9430 0.01388 0.00810 0.0116 0.0036 1.0000
8.500 0.9657 0.01439 0.00866 0.0121 0.0034 1.0000
8.750 0.9878 0.01496 0.00930 0.0127 0.0033 1.0000
9.000 1.0091 0.01560 0.01000 0.0133 0.0032 1.0000
9.250 1.0297 0.01626 0.01073 0.0141 0.0030 1.0000
9.500 1.0495 0.01697 0.01151 0.0149 0.0029 1.0000
9.750 1.0683 0.01773 0.01235 0.0158 0.0028 1.0000
10.000 1.0861 0.01853 0.01323 0.0168 0.0027 1.0000
10.250 1.1025 0.01940 0.01418 0.0179 0.0026 1.0000
10.500 1.1175 0.02032 0.01518 0.0191 0.0026 1.0000
10.750 1.1300 0.02136 0.01631 0.0206 0.0025 1.0000
11.000 1.1400 0.02249 0.01752 0.0223 0.0024 1.0000
11.250 1.1475 0.02369 0.01882 0.0242 0.0024 1.0000
11.500 1.1442 0.02502 0.02023 0.0271 0.0023 1.0000
11.750 1.1380 0.02679 0.02210 0.0295 0.0023 1.0000
12.000 1.1369 0.02873 0.02414 0.0306 0.0023 1.0000
12.250 1.1323 0.03128 0.02681 0.0314 0.0022 1.0000
12.500 1.1224 0.03458 0.03026 0.0319 0.0021 1.0000
12.750 1.1173 0.03755 0.03335 0.0321 0.0021 1.0000
13.000 1.1120 0.04066 0.03658 0.0320 0.0021 1.0000
13.250 1.1156 0.04290 0.03890 0.0317 0.0021 1.0000
13.500 1.1089 0.04637 0.04251 0.0312 0.0021 1.0000
13.750 1.1075 0.04933 0.04558 0.0306 0.0021 1.0000
14.000 1.1029 0.05276 0.04911 0.0297 0.0021 1.0000
14.250 1.0918 0.05714 0.05363 0.0285 0.0021 1.0000
14.500 1.0839 0.06130 0.05791 0.0271 0.0020 1.0000
14.750 1.0778 0.06546 0.06217 0.0254 0.0020 1.0000
15.000 1.0689 0.07025 0.06708 0.0234 0.0020 1.0000
15.250 1.0527 0.07640 0.07337 0.0208 0.0020 1.0000
15.500 1.0411 0.08206 0.07914 0.0182 0.0020 1.0000
15.750 1.0263 0.08851 0.08571 0.0152 0.0021 1.0000
16.000 1.0182 0.09404 0.09134 0.0125 0.0020 1.0000
16.250 0.9986 0.10181 0.09923 0.0088 0.0020 1.0000
16.500 0.9810 0.10952 0.10706 0.0052 0.0021 1.0000
16.750 0.9669 0.11677 0.11441 0.0017 0.0021 1.0000
17.000 0.9431 0.12638 0.12414 -0.0029 0.0021 1.0000
17.250 0.9172 0.13694 0.13482 -0.0078 0.0021 1.0000
17.500 0.9088 0.14356 0.14150 -0.0109 0.0021 1.0000
17.750 0.8779 0.15638 0.15442 -0.0168 0.0021 1.0000
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Polar data table (+)
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