E216 (10.4%) (e216-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: E216 (10.4%) (e216-il) Reynolds number: 50,000 Max Cl/Cd: 42.99 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e216-il-50000-n5.txt Download as CSV file: xf-e216-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E216 (10.4%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3374 0.12223 0.11543 -0.0317 1.0000 0.1008
-8.500 -0.3393 0.11988 0.11314 -0.0311 1.0000 0.1019
-8.000 -0.3725 0.11085 0.10429 -0.0348 1.0000 0.0553
-7.750 -0.3693 0.10821 0.10169 -0.0329 1.0000 0.0547
-7.500 -0.3736 0.10572 0.09926 -0.0316 1.0000 0.0543
-7.250 -0.3777 0.10340 0.09702 -0.0301 1.0000 0.0536
-7.000 -0.3847 0.10113 0.09484 -0.0285 1.0000 0.0528
-6.750 -0.3937 0.09893 0.09273 -0.0269 1.0000 0.0521
-6.500 -0.4015 0.09639 0.09028 -0.0260 1.0000 0.0512
-6.250 -0.4075 0.09344 0.08741 -0.0261 1.0000 0.0502
-6.000 -0.4123 0.08996 0.08402 -0.0273 1.0000 0.0492
-5.750 -0.4148 0.08564 0.07976 -0.0300 1.0000 0.0481
-5.500 -0.3992 0.07264 0.06664 -0.0486 0.9981 0.0445
-5.250 -0.3684 0.06537 0.05917 -0.0593 0.9933 0.0441
-5.000 -0.3277 0.05697 0.05036 -0.0728 0.9891 0.0436
-4.750 -0.2737 0.04849 0.04111 -0.0876 0.9869 0.0436
-4.500 -0.2151 0.04187 0.03341 -0.0994 0.9856 0.0447
-4.250 -0.1769 0.03958 0.03094 -0.1038 0.9817 0.0483
-4.000 -0.1310 0.03682 0.02754 -0.1091 0.9788 0.0526
-3.750 -0.0867 0.03451 0.02465 -0.1131 0.9763 0.0563
-3.500 -0.0499 0.03322 0.02319 -0.1157 0.9718 0.0638
-3.250 -0.0111 0.03204 0.02182 -0.1184 0.9677 0.0765
-3.000 0.0294 0.03101 0.02073 -0.1217 0.9638 0.1035
-2.750 0.0694 0.03014 0.01992 -0.1250 0.9588 0.1544
-2.500 0.1125 0.02960 0.01951 -0.1288 0.9548 0.2197
-2.250 0.1484 0.02934 0.01933 -0.1311 0.9484 0.2822
-2.000 0.1871 0.02925 0.01929 -0.1336 0.9431 0.3451
-1.750 0.2199 0.02923 0.01930 -0.1349 0.9361 0.3989
-1.500 0.2559 0.02926 0.01935 -0.1365 0.9301 0.4537
-1.250 0.2864 0.02930 0.01941 -0.1371 0.9224 0.5020
-1.000 0.3206 0.02933 0.01944 -0.1383 0.9159 0.5510
-0.750 0.3478 0.02937 0.01953 -0.1381 0.9073 0.5945
-0.500 0.3809 0.02936 0.01953 -0.1388 0.9008 0.6415
-0.250 0.4045 0.02939 0.01958 -0.1378 0.8911 0.6844
0.000 0.4362 0.02924 0.01947 -0.1380 0.8851 0.7331
0.500 0.4729 0.02900 0.01933 -0.1337 0.8647 0.8373
0.750 0.4964 0.02835 0.01872 -0.1323 0.8559 1.0000
1.250 0.5691 0.02883 0.01883 -0.1367 0.8372 1.0000
1.500 0.6053 0.02898 0.01884 -0.1385 0.8281 1.0000
1.750 0.6370 0.02922 0.01898 -0.1396 0.8176 1.0000
2.000 0.6784 0.02911 0.01878 -0.1418 0.8110 1.0000
2.250 0.7068 0.02937 0.01899 -0.1421 0.7992 1.0000
2.500 0.7393 0.02946 0.01905 -0.1430 0.7891 1.0000
2.750 0.7779 0.02925 0.01883 -0.1444 0.7813 1.0000
3.000 0.8064 0.02943 0.01901 -0.1446 0.7692 1.0000
3.250 0.8391 0.02941 0.01901 -0.1452 0.7587 1.0000
3.500 0.8785 0.02906 0.01872 -0.1465 0.7502 1.0000
3.750 0.9072 0.02917 0.01887 -0.1465 0.7372 1.0000
4.000 0.9379 0.02918 0.01893 -0.1466 0.7246 1.0000
4.250 0.9714 0.02905 0.01890 -0.1471 0.7125 1.0000
4.500 1.0093 0.02870 0.01863 -0.1480 0.7011 1.0000
4.750 1.0448 0.02848 0.01849 -0.1487 0.6878 1.0000
5.000 1.0764 0.02844 0.01856 -0.1488 0.6726 1.0000
5.250 1.1088 0.02837 0.01859 -0.1490 0.6568 1.0000
5.500 1.1371 0.02849 0.01880 -0.1486 0.6390 1.0000
5.750 1.1638 0.02869 0.01913 -0.1479 0.6201 1.0000
6.000 1.1921 0.02883 0.01935 -0.1475 0.6005 1.0000
6.250 1.2230 0.02890 0.01949 -0.1473 0.5803 1.0000
6.500 1.2464 0.02927 0.01997 -0.1462 0.5586 1.0000
6.750 1.2704 0.02964 0.02042 -0.1451 0.5361 1.0000
7.000 1.2930 0.03008 0.02091 -0.1438 0.5131 1.0000
7.250 1.3125 0.03064 0.02154 -0.1421 0.4892 1.0000
7.500 1.3306 0.03129 0.02226 -0.1402 0.4649 1.0000
7.750 1.3479 0.03198 0.02298 -0.1382 0.4405 1.0000
8.000 1.3612 0.03287 0.02393 -0.1358 0.4157 1.0000
8.250 1.3752 0.03377 0.02482 -0.1335 0.3913 1.0000
8.500 1.3856 0.03485 0.02601 -0.1308 0.3668 1.0000
8.750 1.3955 0.03601 0.02718 -0.1282 0.3428 1.0000
9.000 1.4036 0.03731 0.02852 -0.1255 0.3191 1.0000
9.250 1.4105 0.03875 0.02999 -0.1227 0.2961 1.0000
9.500 1.4160 0.04032 0.03159 -0.1200 0.2738 1.0000
9.750 1.4206 0.04205 0.03334 -0.1173 0.2526 1.0000
10.000 1.4241 0.04395 0.03532 -0.1148 0.2318 1.0000
10.250 1.4266 0.04600 0.03740 -0.1123 0.2130 1.0000
10.500 1.4280 0.04825 0.03965 -0.1100 0.1951 1.0000
10.750 1.4293 0.05065 0.04215 -0.1079 0.1779 1.0000
11.000 1.4292 0.05327 0.04483 -0.1059 0.1619 1.0000
11.250 1.4283 0.05608 0.04771 -0.1041 0.1472 1.0000
11.500 1.4257 0.05915 0.05085 -0.1025 0.1334 1.0000
11.750 1.4214 0.06249 0.05425 -0.1012 0.1205 1.0000
12.000 1.4153 0.06613 0.05797 -0.1002 0.1085 1.0000
12.250 1.4084 0.07003 0.06188 -0.0996 0.0982 1.0000
12.500 1.4018 0.07413 0.06611 -0.0993 0.0881 1.0000
12.750 1.3964 0.07834 0.07047 -0.0992 0.0792 1.0000
13.000 1.3903 0.08271 0.07489 -0.0994 0.0728 1.0000
13.250 1.3859 0.08712 0.07949 -0.0996 0.0663 1.0000
13.500 1.3812 0.09155 0.08397 -0.1001 0.0618 1.0000
13.750 1.3785 0.09604 0.08874 -0.1006 0.0570 1.0000
14.000 1.3756 0.10037 0.09314 -0.1013 0.0538 1.0000
14.250 1.3738 0.10481 0.09775 -0.1021 0.0509 1.0000
14.500 1.3696 0.10990 0.10316 -0.1035 0.0483 1.0000
14.750 1.3647 0.11505 0.10852 -0.1053 0.0461 1.0000
15.000 1.3617 0.11977 0.11334 -0.1071 0.0443 1.0000
15.250 1.3602 0.12427 0.11792 -0.1087 0.0428 1.0000
15.500 1.3502 0.13116 0.12516 -0.1122 0.0420 1.0000
15.750 1.3378 0.13885 0.13313 -0.1166 0.0415 1.0000
16.000 1.3229 0.14754 0.14209 -0.1220 0.0413 1.0000
16.250 1.3052 0.15755 0.15234 -0.1287 0.0413 1.0000
16.500 1.2849 0.16925 0.16422 -0.1367 0.0416 1.0000
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Polar data table (+)
Polar graphs
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