E216 (10.4%) (e216-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: E216 (10.4%) (e216-il) Reynolds number: 100,000 Max Cl/Cd: 68.5 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e216-il-100000.txt Download as CSV file: xf-e216-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-6.750 -0.3889 0.10382 0.09960 -0.0197 1.0000 0.1018
-6.500 -0.4111 0.10310 0.09899 -0.0179 1.0000 0.1034
-6.250 -0.4341 0.10190 0.09790 -0.0212 1.0000 0.1046
-6.000 -0.4393 0.09802 0.09410 -0.0226 1.0000 0.1060
-5.750 -0.4298 0.09566 0.09175 -0.0156 1.0000 0.1084
-5.500 -0.4287 0.09346 0.08958 -0.0140 1.0000 0.1114
-5.250 -0.4247 0.08715 0.08327 -0.0376 1.0000 0.1199
-5.000 -0.4265 0.08498 0.08118 -0.0292 1.0000 0.1209
-4.750 -0.4245 0.08313 0.07936 -0.0238 1.0000 0.1227
-4.500 -0.4020 0.07823 0.07439 -0.0361 1.0000 0.1338
-4.250 -0.3900 0.07409 0.07027 -0.0373 0.9990 0.1368
-4.000 -0.2319 0.04133 0.03529 -0.0917 1.0000 0.0636
-3.750 -0.1694 0.03563 0.02897 -0.1016 0.9974 0.0606
-3.500 -0.1056 0.03261 0.02502 -0.1096 0.9937 0.0629
-3.250 -0.0531 0.03017 0.02212 -0.1151 0.9896 0.0663
-3.000 -0.0035 0.02900 0.02072 -0.1193 0.9860 0.0726
-2.750 0.0408 0.02799 0.01962 -0.1228 0.9801 0.0884
-2.500 0.0924 0.02687 0.01870 -0.1278 0.9766 0.1499
-2.250 0.1361 0.02658 0.01872 -0.1318 0.9701 0.2422
-2.000 0.1813 0.02655 0.01893 -0.1356 0.9649 0.3221
-1.750 0.2177 0.02657 0.01910 -0.1377 0.9567 0.3868
-1.500 0.2582 0.02672 0.01937 -0.1403 0.9505 0.4498
-1.250 0.2943 0.02681 0.01957 -0.1420 0.9424 0.5042
-1.000 0.3285 0.02693 0.01976 -0.1432 0.9343 0.5557
-0.750 0.3681 0.02699 0.01991 -0.1452 0.9279 0.6077
-0.500 0.3976 0.02706 0.02007 -0.1454 0.9184 0.6532
-0.250 0.4375 0.02699 0.02007 -0.1471 0.9130 0.7031
0.000 0.4616 0.02699 0.02014 -0.1461 0.9022 0.7469
0.250 0.4884 0.02687 0.02009 -0.1453 0.8936 0.7942
0.500 0.5148 0.02651 0.01979 -0.1441 0.8858 0.8497
0.750 0.5249 0.02598 0.01939 -0.1401 0.8742 0.9404
1.000 0.5842 0.02565 0.01887 -0.1465 0.8696 1.0000
1.250 0.6201 0.02580 0.01890 -0.1487 0.8584 1.0000
1.500 0.6715 0.02544 0.01842 -0.1528 0.8537 1.0000
1.750 0.7053 0.02546 0.01838 -0.1541 0.8428 1.0000
2.000 0.7418 0.02535 0.01822 -0.1556 0.8332 1.0000
2.250 0.7892 0.02473 0.01756 -0.1585 0.8274 1.0000
2.500 0.8244 0.02449 0.01732 -0.1595 0.8173 1.0000
2.750 0.8744 0.02353 0.01636 -0.1625 0.8124 1.0000
3.000 0.9109 0.02314 0.01599 -0.1635 0.8021 1.0000
3.250 0.9650 0.02202 0.01493 -0.1672 0.7969 1.0000
3.500 1.0026 0.02159 0.01454 -0.1684 0.7852 1.0000
3.750 1.0517 0.02080 0.01379 -0.1714 0.7758 1.0000
4.000 1.1030 0.01992 0.01298 -0.1747 0.7654 1.0000
4.250 1.1424 0.01950 0.01259 -0.1761 0.7504 1.0000
4.500 1.1794 0.01920 0.01234 -0.1770 0.7335 1.0000
4.750 1.2089 0.01917 0.01234 -0.1767 0.7136 1.0000
5.000 1.2420 0.01908 0.01225 -0.1770 0.6935 1.0000
5.250 1.2758 0.01904 0.01221 -0.1775 0.6726 1.0000
5.500 1.3002 0.01926 0.01244 -0.1763 0.6489 1.0000
5.750 1.3276 0.01944 0.01259 -0.1756 0.6251 1.0000
6.000 1.3516 0.01973 0.01285 -0.1744 0.5997 1.0000
6.250 1.3729 0.02012 0.01324 -0.1728 0.5735 1.0000
6.500 1.3944 0.02054 0.01361 -0.1712 0.5471 1.0000
6.750 1.4149 0.02102 0.01401 -0.1694 0.5202 1.0000
7.000 1.4317 0.02158 0.01456 -0.1671 0.4920 1.0000
7.250 1.4473 0.02219 0.01515 -0.1646 0.4634 1.0000
7.500 1.4616 0.02287 0.01578 -0.1619 0.4345 1.0000
7.750 1.4744 0.02363 0.01648 -0.1590 0.4055 1.0000
8.000 1.4856 0.02446 0.01725 -0.1559 0.3766 1.0000
8.250 1.4948 0.02537 0.01810 -0.1526 0.3481 1.0000
8.500 1.5019 0.02638 0.01901 -0.1489 0.3208 1.0000
8.750 1.5075 0.02749 0.02004 -0.1452 0.2936 1.0000
9.000 1.5122 0.02871 0.02123 -0.1414 0.2667 1.0000
9.250 1.5152 0.03007 0.02251 -0.1376 0.2403 1.0000
9.500 1.5164 0.03156 0.02390 -0.1338 0.2153 1.0000
9.750 1.5162 0.03316 0.02541 -0.1300 0.1910 1.0000
10.000 1.5165 0.03487 0.02713 -0.1265 0.1670 1.0000
10.250 1.5155 0.03690 0.02903 -0.1232 0.1473 1.0000
10.500 1.5161 0.03902 0.03119 -0.1201 0.1268 1.0000
10.750 1.5132 0.04150 0.03361 -0.1170 0.1089 1.0000
11.000 1.5084 0.04443 0.03645 -0.1140 0.0922 1.0000
11.250 1.5047 0.04757 0.03960 -0.1112 0.0773 1.0000
11.500 1.5039 0.05078 0.04274 -0.1087 0.0674 1.0000
11.750 1.5077 0.05356 0.04558 -0.1068 0.0602 1.0000
12.000 1.5168 0.05643 0.04854 -0.1051 0.0547 1.0000
12.250 1.5238 0.05905 0.05128 -0.1037 0.0505 1.0000
12.500 1.5461 0.06198 0.05417 -0.1029 0.0470 1.0000
12.750 1.5571 0.06504 0.05758 -0.1015 0.0452 1.0000
13.000 1.5663 0.06846 0.06131 -0.1002 0.0439 1.0000
13.250 1.5706 0.07220 0.06536 -0.0988 0.0428 1.0000
13.500 1.5706 0.07612 0.06958 -0.0975 0.0420 1.0000
13.750 1.5659 0.08030 0.07405 -0.0964 0.0413 1.0000
14.000 1.5581 0.08470 0.07871 -0.0956 0.0407 1.0000
14.250 1.5491 0.08918 0.08343 -0.0952 0.0401 1.0000
14.500 1.5397 0.09401 0.08847 -0.0952 0.0395 1.0000
14.750 1.5258 0.09940 0.09412 -0.0958 0.0393 1.0000
15.000 1.5057 0.10547 0.10051 -0.0972 0.0394 1.0000
15.250 1.4873 0.11178 0.10708 -0.0993 0.0392 1.0000
15.500 1.4508 0.12120 0.11695 -0.1042 0.0403 1.0000
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Polar data table (+)
Polar graphs
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