E216 (10.4%) (e216-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: E216 (10.4%) (e216-il) Reynolds number: 1,000,000 Max Cl/Cd: 155.1 at α=1.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e216-il-1000000.txt Download as CSV file: xf-e216-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.2318 0.10024 0.09851 -0.0715 0.9859 0.0126
-9.500 -0.2288 0.09638 0.09466 -0.0727 0.9818 0.0126
-9.250 -0.2268 0.09033 0.08863 -0.0768 0.9796 0.0128
-9.000 -0.2131 0.08764 0.08594 -0.0795 0.9784 0.0131
-8.750 -0.1983 0.08446 0.08275 -0.0830 0.9773 0.0133
-8.500 -0.1830 0.08092 0.07921 -0.0871 0.9764 0.0137
-8.250 -0.1676 0.07687 0.07517 -0.0920 0.9756 0.0140
-7.500 -0.1549 0.01946 0.01584 -0.1660 0.9529 0.0097
-7.250 -0.1337 0.01802 0.01420 -0.1658 0.9474 0.0097
-7.000 -0.0978 0.01540 0.01125 -0.1693 0.9462 0.0098
-6.750 -0.0624 0.01391 0.00964 -0.1719 0.9452 0.0103
-6.500 -0.0271 0.01305 0.00869 -0.1739 0.9443 0.0107
-6.250 0.0085 0.01225 0.00781 -0.1760 0.9435 0.0111
-6.000 0.0444 0.01151 0.00699 -0.1780 0.9427 0.0114
-5.750 0.0805 0.01082 0.00622 -0.1800 0.9421 0.0117
-5.500 0.1172 0.01019 0.00553 -0.1821 0.9414 0.0121
-5.250 0.1543 0.00965 0.00492 -0.1842 0.9407 0.0124
-5.000 0.1924 0.00904 0.00424 -0.1866 0.9400 0.0130
-4.750 0.2173 0.00859 0.00374 -0.1861 0.9342 0.0139
-4.500 0.2524 0.00818 0.00330 -0.1877 0.9317 0.0150
-4.250 0.2888 0.00785 0.00291 -0.1895 0.9296 0.0163
-4.000 0.3289 0.00744 0.00248 -0.1922 0.9280 0.0204
-3.750 0.3723 0.00690 0.00213 -0.1959 0.9266 0.0657
-3.500 0.3989 0.00666 0.00198 -0.1957 0.9194 0.0962
-3.250 0.4389 0.00638 0.00181 -0.1985 0.9159 0.1366
-3.000 0.4821 0.00613 0.00166 -0.2021 0.9127 0.1775
-2.750 0.5118 0.00596 0.00158 -0.2025 0.9045 0.2151
-2.500 0.5506 0.00578 0.00148 -0.2050 0.8988 0.2584
-2.250 0.5807 0.00569 0.00143 -0.2055 0.8897 0.2884
-2.000 0.6143 0.00561 0.00137 -0.2068 0.8814 0.3184
-1.750 0.6451 0.00555 0.00134 -0.2074 0.8713 0.3501
-1.500 0.6746 0.00551 0.00133 -0.2077 0.8604 0.3769
-1.250 0.7039 0.00551 0.00132 -0.2080 0.8488 0.4011
-1.000 0.7325 0.00552 0.00133 -0.2081 0.8363 0.4265
-0.750 0.7602 0.00555 0.00134 -0.2080 0.8228 0.4500
-0.500 0.7872 0.00559 0.00137 -0.2077 0.8084 0.4749
-0.250 0.8137 0.00565 0.00141 -0.2074 0.7935 0.4982
0.000 0.8399 0.00572 0.00147 -0.2069 0.7779 0.5216
0.250 0.8657 0.00580 0.00153 -0.2064 0.7619 0.5437
0.500 0.8914 0.00589 0.00160 -0.2059 0.7454 0.5658
0.750 0.9167 0.00600 0.00168 -0.2053 0.7281 0.5879
1.000 0.9419 0.00611 0.00177 -0.2047 0.7102 0.6098
1.250 0.9665 0.00625 0.00188 -0.2039 0.6915 0.6323
1.500 0.9911 0.00640 0.00199 -0.2032 0.6723 0.6541
1.750 1.0159 0.00655 0.00211 -0.2025 0.6524 0.6764
2.250 1.0647 0.00689 0.00239 -0.2010 0.6134 0.7206
2.500 1.0893 0.00706 0.00254 -0.2002 0.5939 0.7432
2.750 1.1135 0.00725 0.00270 -0.1995 0.5728 0.7652
3.000 1.1370 0.00747 0.00288 -0.1985 0.5511 0.7879
3.250 1.1608 0.00768 0.00305 -0.1977 0.5286 0.8109
3.500 1.1839 0.00792 0.00324 -0.1967 0.5063 0.8347
3.750 1.2068 0.00813 0.00343 -0.1956 0.4847 0.8590
4.000 1.2285 0.00836 0.00364 -0.1943 0.4626 0.8858
4.250 1.2480 0.00856 0.00381 -0.1925 0.4420 0.9196
4.500 1.2654 0.00871 0.00394 -0.1902 0.4205 1.0000
4.750 1.2891 0.00905 0.00417 -0.1895 0.3973 1.0000
5.000 1.3120 0.00945 0.00444 -0.1886 0.3695 1.0000
5.250 1.3339 0.00991 0.00474 -0.1875 0.3372 1.0000
5.500 1.3553 0.01039 0.00505 -0.1864 0.3049 1.0000
5.750 1.3765 0.01086 0.00539 -0.1852 0.2768 1.0000
6.000 1.3979 0.01130 0.00571 -0.1841 0.2520 1.0000
6.250 1.4183 0.01180 0.00608 -0.1828 0.2256 1.0000
6.500 1.4377 0.01236 0.00649 -0.1813 0.1975 1.0000
6.750 1.4568 0.01293 0.00692 -0.1797 0.1729 1.0000
7.000 1.4754 0.01350 0.00737 -0.1781 0.1496 1.0000
7.250 1.4940 0.01406 0.00783 -0.1765 0.1292 1.0000
7.500 1.5113 0.01472 0.00835 -0.1746 0.1076 1.0000
7.750 1.5291 0.01533 0.00887 -0.1729 0.0897 1.0000
8.000 1.5459 0.01599 0.00944 -0.1710 0.0734 1.0000
8.250 1.5615 0.01672 0.01007 -0.1689 0.0574 1.0000
8.500 1.5762 0.01752 0.01077 -0.1667 0.0414 1.0000
8.750 1.5876 0.01858 0.01169 -0.1640 0.0230 1.0000
9.000 1.5996 0.01957 0.01262 -0.1613 0.0135 1.0000
9.250 1.6143 0.02036 0.01343 -0.1591 0.0114 1.0000
9.500 1.6297 0.02110 0.01422 -0.1571 0.0105 1.0000
9.750 1.6449 0.02183 0.01501 -0.1551 0.0100 1.0000
10.000 1.6593 0.02264 0.01588 -0.1530 0.0095 1.0000
10.250 1.6722 0.02355 0.01684 -0.1508 0.0090 1.0000
10.500 1.6835 0.02461 0.01798 -0.1483 0.0086 1.0000
10.750 1.6917 0.02590 0.01937 -0.1455 0.0082 1.0000
11.000 1.7008 0.02714 0.02070 -0.1429 0.0080 1.0000
11.250 1.7119 0.02824 0.02187 -0.1407 0.0079 1.0000
11.500 1.7216 0.02944 0.02316 -0.1384 0.0077 1.0000
11.750 1.7309 0.03070 0.02450 -0.1362 0.0075 1.0000
12.000 1.7389 0.03211 0.02599 -0.1339 0.0073 1.0000
12.250 1.7457 0.03366 0.02763 -0.1316 0.0071 1.0000
12.500 1.7510 0.03538 0.02944 -0.1293 0.0069 1.0000
12.750 1.7553 0.03724 0.03139 -0.1270 0.0068 1.0000
13.000 1.7583 0.03929 0.03354 -0.1248 0.0066 1.0000
13.250 1.7600 0.04154 0.03589 -0.1228 0.0065 1.0000
13.500 1.7587 0.04420 0.03866 -0.1207 0.0064 1.0000
13.750 1.7570 0.04704 0.04160 -0.1189 0.0063 1.0000
14.000 1.7519 0.05041 0.04510 -0.1172 0.0062 1.0000
14.250 1.7433 0.05438 0.04920 -0.1157 0.0061 1.0000
14.500 1.7324 0.05888 0.05385 -0.1146 0.0060 1.0000
14.750 1.7215 0.06365 0.05876 -0.1140 0.0059 1.0000
15.250 1.7090 0.07243 0.06781 -0.1138 0.0058 1.0000
15.500 1.7049 0.07675 0.07225 -0.1141 0.0058 1.0000
15.750 1.7022 0.08098 0.07660 -0.1147 0.0058 1.0000
16.000 1.6961 0.08587 0.08161 -0.1156 0.0057 1.0000
16.250 1.6893 0.09100 0.08687 -0.1167 0.0057 1.0000
16.500 1.6832 0.09615 0.09215 -0.1181 0.0057 1.0000
16.750 1.6778 0.10130 0.09743 -0.1198 0.0056 1.0000
17.000 1.6697 0.10700 0.10326 -0.1217 0.0056 1.0000
17.250 1.6622 0.11269 0.10908 -0.1239 0.0055 1.0000
17.500 1.6555 0.11832 0.11483 -0.1263 0.0055 1.0000
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Polar data table (+)
Polar graphs
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