EPPLER 66 AIRFOIL (e66-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 66 AIRFOIL (e66-il) Reynolds number: 500,000 Max Cl/Cd: 113.47 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e66-il-500000-n5.txt Download as CSV file: xf-e66-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 66 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3750 0.10202 0.09968 -0.0471 0.9956 0.0059
-10.250 -0.3739 0.09541 0.09309 -0.0516 0.9943 0.0060
-9.750 -0.5181 0.03444 0.03160 -0.1114 0.9718 0.0053
-9.500 -0.5129 0.02925 0.02594 -0.1155 0.9633 0.0054
-9.250 -0.4893 0.02585 0.02213 -0.1192 0.9607 0.0056
-9.000 -0.4665 0.02344 0.01938 -0.1210 0.9574 0.0058
-8.750 -0.4449 0.02192 0.01759 -0.1214 0.9526 0.0060
-8.500 -0.4180 0.02006 0.01543 -0.1229 0.9500 0.0061
-8.250 -0.3899 0.01799 0.01307 -0.1247 0.9482 0.0065
-8.000 -0.3588 0.01682 0.01173 -0.1263 0.9469 0.0068
-7.750 -0.3335 0.01598 0.01076 -0.1264 0.9430 0.0071
-7.500 -0.3062 0.01524 0.00990 -0.1268 0.9393 0.0075
-7.250 -0.2753 0.01441 0.00893 -0.1279 0.9370 0.0080
-7.000 -0.2425 0.01368 0.00806 -0.1294 0.9351 0.0085
-6.750 -0.2085 0.01304 0.00730 -0.1310 0.9336 0.0091
-6.500 -0.1785 0.01235 0.00654 -0.1319 0.9304 0.0101
-6.250 -0.1505 0.01197 0.00611 -0.1321 0.9259 0.0115
-6.000 -0.1184 0.01158 0.00562 -0.1332 0.9228 0.0131
-5.750 -0.0845 0.01102 0.00502 -0.1347 0.9204 0.0154
-5.500 -0.0527 0.01067 0.00459 -0.1357 0.9170 0.0177
-5.250 -0.0242 0.01030 0.00418 -0.1360 0.9117 0.0204
-5.000 0.0081 0.01000 0.00382 -0.1370 0.9078 0.0239
-4.750 0.0413 0.00965 0.00347 -0.1383 0.9043 0.0300
-4.500 0.0688 0.00938 0.00320 -0.1384 0.8980 0.0382
-4.250 0.1001 0.00910 0.00293 -0.1392 0.8931 0.0524
-4.000 0.1300 0.00887 0.00270 -0.1397 0.8876 0.0666
-3.750 0.1590 0.00867 0.00251 -0.1400 0.8812 0.0813
-3.500 0.1898 0.00847 0.00232 -0.1407 0.8757 0.0992
-3.250 0.2174 0.00829 0.00219 -0.1408 0.8685 0.1217
-2.750 0.2749 0.00790 0.00194 -0.1413 0.8547 0.1854
-2.500 0.3044 0.00777 0.00183 -0.1417 0.8480 0.2120
-2.250 0.3318 0.00764 0.00175 -0.1417 0.8400 0.2410
-2.000 0.3605 0.00753 0.00168 -0.1419 0.8326 0.2717
-1.750 0.3881 0.00742 0.00163 -0.1419 0.8240 0.3024
-1.500 0.4161 0.00732 0.00158 -0.1420 0.8158 0.3410
-1.250 0.4439 0.00722 0.00155 -0.1420 0.8068 0.3789
-1.000 0.4713 0.00714 0.00154 -0.1419 0.7973 0.4152
-0.750 0.4988 0.00708 0.00153 -0.1419 0.7874 0.4529
-0.250 0.5531 0.00699 0.00155 -0.1415 0.7656 0.5283
0.000 0.5799 0.00695 0.00159 -0.1413 0.7542 0.5669
0.250 0.6065 0.00694 0.00163 -0.1410 0.7423 0.6039
0.500 0.6329 0.00694 0.00168 -0.1406 0.7299 0.6403
0.750 0.6589 0.00695 0.00174 -0.1402 0.7166 0.6761
1.000 0.6844 0.00698 0.00181 -0.1396 0.7025 0.7122
1.250 0.7094 0.00701 0.00189 -0.1389 0.6876 0.7477
1.500 0.7338 0.00706 0.00198 -0.1381 0.6715 0.7831
1.750 0.7574 0.00713 0.00207 -0.1371 0.6550 0.8173
2.000 0.7797 0.00720 0.00218 -0.1357 0.6377 0.8516
2.250 0.8003 0.00728 0.00227 -0.1340 0.6200 0.8882
2.500 0.8193 0.00734 0.00233 -0.1319 0.6016 0.9333
2.750 0.8465 0.00746 0.00239 -0.1317 0.5804 1.0000
3.000 0.8707 0.00769 0.00253 -0.1310 0.5578 1.0000
3.250 0.8944 0.00795 0.00268 -0.1302 0.5331 1.0000
3.500 0.9179 0.00823 0.00285 -0.1294 0.5072 1.0000
3.750 0.9412 0.00852 0.00304 -0.1286 0.4811 1.0000
4.000 0.9641 0.00884 0.00324 -0.1277 0.4535 1.0000
4.250 0.9868 0.00918 0.00347 -0.1267 0.4251 1.0000
4.500 1.0090 0.00956 0.00371 -0.1258 0.3949 1.0000
4.750 1.0306 0.00998 0.00399 -0.1247 0.3625 1.0000
5.000 1.0516 0.01045 0.00431 -0.1235 0.3275 1.0000
5.250 1.0725 0.01093 0.00463 -0.1224 0.2931 1.0000
5.500 1.0940 0.01138 0.00496 -0.1213 0.2649 1.0000
5.750 1.1155 0.01181 0.00530 -0.1203 0.2404 1.0000
6.000 1.1353 0.01237 0.00571 -0.1190 0.2075 1.0000
6.250 1.1543 0.01298 0.00614 -0.1175 0.1745 1.0000
6.500 1.1732 0.01358 0.00659 -0.1161 0.1447 1.0000
6.750 1.1914 0.01421 0.00707 -0.1146 0.1168 1.0000
7.000 1.2102 0.01471 0.00750 -0.1131 0.0994 1.0000
7.250 1.2287 0.01523 0.00796 -0.1115 0.0846 1.0000
7.500 1.2468 0.01575 0.00846 -0.1099 0.0717 1.0000
7.750 1.2647 0.01628 0.00896 -0.1083 0.0607 1.0000
8.000 1.2822 0.01684 0.00949 -0.1066 0.0506 1.0000
8.250 1.2990 0.01744 0.01006 -0.1048 0.0413 1.0000
8.500 1.3152 0.01808 0.01067 -0.1030 0.0331 1.0000
8.750 1.3308 0.01875 0.01133 -0.1011 0.0261 1.0000
9.000 1.3464 0.01942 0.01203 -0.0993 0.0214 1.0000
9.250 1.3616 0.02012 0.01275 -0.0974 0.0180 1.0000
9.500 1.3764 0.02083 0.01349 -0.0955 0.0158 1.0000
9.750 1.3897 0.02166 0.01435 -0.0934 0.0138 1.0000
10.000 1.4047 0.02237 0.01514 -0.0916 0.0130 1.0000
10.250 1.4188 0.02313 0.01599 -0.0898 0.0120 1.0000
10.500 1.4315 0.02401 0.01691 -0.0878 0.0109 1.0000
10.750 1.4419 0.02508 0.01806 -0.0857 0.0098 1.0000
11.000 1.4549 0.02595 0.01901 -0.0839 0.0091 1.0000
11.250 1.4665 0.02694 0.02010 -0.0820 0.0085 1.0000
11.500 1.4773 0.02801 0.02126 -0.0801 0.0079 1.0000
11.750 1.4868 0.02921 0.02253 -0.0782 0.0072 1.0000
12.000 1.4925 0.03076 0.02416 -0.0760 0.0066 1.0000
12.250 1.5015 0.03206 0.02556 -0.0743 0.0063 1.0000
12.500 1.5094 0.03349 0.02711 -0.0725 0.0059 1.0000
12.750 1.5166 0.03502 0.02874 -0.0709 0.0055 1.0000
13.000 1.5226 0.03670 0.03054 -0.0692 0.0052 1.0000
13.250 1.5281 0.03848 0.03241 -0.0678 0.0048 1.0000
13.500 1.5312 0.04055 0.03458 -0.0663 0.0046 1.0000
13.750 1.5313 0.04300 0.03715 -0.0649 0.0043 1.0000
14.000 1.5342 0.04526 0.03954 -0.0638 0.0041 1.0000
14.250 1.5364 0.04767 0.04208 -0.0629 0.0039 1.0000
14.500 1.5365 0.05041 0.04496 -0.0621 0.0038 1.0000
14.750 1.5365 0.05328 0.04795 -0.0616 0.0036 1.0000
15.000 1.5360 0.05634 0.05114 -0.0613 0.0034 1.0000
15.250 1.5353 0.05955 0.05447 -0.0613 0.0033 1.0000
15.500 1.5318 0.06327 0.05833 -0.0615 0.0032 1.0000
15.750 1.5274 0.06728 0.06248 -0.0620 0.0031 1.0000
16.000 1.5211 0.07178 0.06712 -0.0629 0.0030 1.0000
16.250 1.5135 0.07666 0.07214 -0.0642 0.0029 1.0000
16.500 1.5037 0.08211 0.07775 -0.0660 0.0029 1.0000
16.750 1.4921 0.08812 0.08393 -0.0682 0.0028 1.0000
17.000 1.4792 0.09461 0.09058 -0.0709 0.0028 1.0000
17.250 1.4652 0.10156 0.09769 -0.0741 0.0028 1.0000
17.500 1.4498 0.10898 0.10528 -0.0777 0.0027 1.0000
17.750 1.4343 0.11668 0.11315 -0.0817 0.0027 1.0000
18.000 1.4188 0.12460 0.12122 -0.0861 0.0027 1.0000
18.250 1.4032 0.13269 0.12947 -0.0907 0.0027 1.0000
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