E216 (10.4%) (e216-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: E216 (10.4%) (e216-il) Reynolds number: 1,000,000 Max Cl/Cd: 127.41 at α=2.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e216-il-1000000-n5.txt Download as CSV file: xf-e216-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.2998 0.06818 0.06633 -0.0997 0.9767 0.0055
-9.750 -0.4042 0.02967 0.02722 -0.1434 0.9560 0.0050
-9.500 -0.3707 0.02444 0.02156 -0.1550 0.9544 0.0052
-9.250 -0.3524 0.02183 0.01869 -0.1574 0.9487 0.0053
-9.000 -0.3228 0.01990 0.01652 -0.1605 0.9465 0.0054
-8.750 -0.2913 0.01822 0.01462 -0.1633 0.9450 0.0055
-8.500 -0.2589 0.01680 0.01301 -0.1659 0.9439 0.0056
-8.250 -0.2262 0.01585 0.01190 -0.1679 0.9429 0.0057
-8.000 -0.1926 0.01492 0.01084 -0.1700 0.9420 0.0058
-7.750 -0.1640 0.01408 0.00987 -0.1709 0.9390 0.0058
-7.500 -0.1346 0.01297 0.00861 -0.1722 0.9355 0.0060
-7.250 -0.1019 0.01210 0.00762 -0.1740 0.9332 0.0062
-7.000 -0.0674 0.01139 0.00683 -0.1759 0.9315 0.0063
-6.750 -0.0316 0.01082 0.00618 -0.1780 0.9301 0.0065
-6.500 0.0055 0.01029 0.00559 -0.1803 0.9288 0.0067
-6.250 0.0375 0.00990 0.00514 -0.1814 0.9253 0.0070
-6.000 0.0699 0.00951 0.00470 -0.1826 0.9213 0.0074
-5.750 0.1063 0.00910 0.00422 -0.1847 0.9183 0.0077
-5.500 0.1454 0.00870 0.00376 -0.1873 0.9158 0.0080
-5.250 0.1846 0.00838 0.00338 -0.1899 0.9130 0.0083
-5.000 0.2187 0.00802 0.00296 -0.1915 0.9073 0.0088
-4.750 0.2587 0.00774 0.00263 -0.1943 0.9026 0.0094
-4.500 0.2967 0.00753 0.00237 -0.1966 0.8971 0.0102
-4.250 0.3309 0.00737 0.00214 -0.1980 0.8891 0.0110
-4.000 0.3652 0.00720 0.00193 -0.1994 0.8811 0.0129
-3.750 0.3984 0.00701 0.00174 -0.2007 0.8717 0.0229
-3.500 0.4296 0.00681 0.00158 -0.2015 0.8614 0.0458
-3.250 0.4605 0.00665 0.00146 -0.2023 0.8504 0.0718
-3.000 0.4900 0.00655 0.00137 -0.2027 0.8383 0.0951
-2.750 0.5189 0.00645 0.00130 -0.2030 0.8251 0.1276
-2.500 0.5470 0.00637 0.00126 -0.2031 0.8114 0.1590
-2.250 0.5747 0.00632 0.00123 -0.2031 0.7975 0.1894
-2.000 0.6020 0.00630 0.00121 -0.2030 0.7831 0.2183
-1.750 0.6290 0.00629 0.00122 -0.2029 0.7682 0.2500
-1.500 0.6555 0.00632 0.00123 -0.2026 0.7527 0.2726
-1.250 0.6816 0.00638 0.00125 -0.2022 0.7364 0.2945
-1.000 0.7075 0.00645 0.00128 -0.2018 0.7195 0.3139
-0.750 0.7334 0.00652 0.00132 -0.2013 0.7021 0.3358
-0.500 0.7593 0.00660 0.00138 -0.2009 0.6843 0.3582
-0.250 0.7853 0.00669 0.00144 -0.2005 0.6663 0.3803
0.000 0.8112 0.00680 0.00151 -0.2001 0.6483 0.4019
0.250 0.8369 0.00691 0.00159 -0.1996 0.6302 0.4223
0.500 0.8628 0.00704 0.00168 -0.1992 0.6124 0.4422
0.750 0.8885 0.00717 0.00178 -0.1988 0.5945 0.4622
1.000 0.9145 0.00730 0.00188 -0.1984 0.5764 0.4825
1.250 0.9403 0.00745 0.00199 -0.1980 0.5573 0.5037
1.500 0.9657 0.00763 0.00212 -0.1975 0.5361 0.5238
1.750 0.9910 0.00782 0.00226 -0.1970 0.5154 0.5442
2.000 1.0167 0.00799 0.00241 -0.1966 0.4956 0.5653
2.250 1.0422 0.00818 0.00256 -0.1962 0.4759 0.5858
2.500 1.0677 0.00838 0.00272 -0.1957 0.4569 0.6059
2.750 1.0929 0.00859 0.00290 -0.1952 0.4373 0.6268
3.000 1.1180 0.00881 0.00308 -0.1947 0.4163 0.6477
3.250 1.1425 0.00909 0.00329 -0.1941 0.3932 0.6678
3.500 1.1673 0.00933 0.00349 -0.1936 0.3723 0.6886
3.750 1.1919 0.00958 0.00372 -0.1930 0.3525 0.7098
4.000 1.2161 0.00987 0.00395 -0.1923 0.3317 0.7312
4.250 1.2402 0.01014 0.00420 -0.1916 0.3117 0.7534
4.500 1.2641 0.01043 0.00445 -0.1909 0.2922 0.7760
4.750 1.2866 0.01081 0.00476 -0.1899 0.2662 0.7994
5.000 1.3074 0.01130 0.00512 -0.1886 0.2320 0.8233
5.250 1.3268 0.01187 0.00553 -0.1871 0.1956 0.8481
5.500 1.3472 0.01226 0.00588 -0.1857 0.1729 0.8756
5.750 1.3655 0.01260 0.00619 -0.1838 0.1550 0.9097
6.000 1.3794 0.01288 0.00646 -0.1809 0.1379 1.0000
6.250 1.3998 0.01337 0.00684 -0.1796 0.1181 1.0000
6.500 1.4187 0.01395 0.00730 -0.1780 0.0967 1.0000
6.750 1.4382 0.01446 0.00773 -0.1766 0.0811 1.0000
7.000 1.4575 0.01497 0.00817 -0.1751 0.0679 1.0000
7.250 1.4760 0.01554 0.00866 -0.1734 0.0546 1.0000
7.500 1.4935 0.01618 0.00922 -0.1716 0.0407 1.0000
7.750 1.5112 0.01677 0.00976 -0.1699 0.0311 1.0000
8.000 1.5274 0.01747 0.01039 -0.1679 0.0210 1.0000
8.250 1.5423 0.01827 0.01113 -0.1657 0.0110 1.0000
8.500 1.5599 0.01886 0.01174 -0.1640 0.0090 1.0000
8.750 1.5768 0.01947 0.01238 -0.1621 0.0078 1.0000
9.000 1.5944 0.02003 0.01298 -0.1605 0.0073 1.0000
9.250 1.6116 0.02063 0.01362 -0.1588 0.0070 1.0000
9.500 1.6277 0.02129 0.01432 -0.1569 0.0066 1.0000
9.750 1.6432 0.02199 0.01508 -0.1550 0.0063 1.0000
10.000 1.6579 0.02277 0.01590 -0.1530 0.0060 1.0000
10.250 1.6714 0.02363 0.01682 -0.1508 0.0058 1.0000
10.500 1.6844 0.02454 0.01779 -0.1487 0.0056 1.0000
10.750 1.6979 0.02540 0.01871 -0.1466 0.0055 1.0000
11.000 1.7108 0.02631 0.01970 -0.1446 0.0054 1.0000
11.250 1.7229 0.02731 0.02076 -0.1425 0.0053 1.0000
11.500 1.7342 0.02837 0.02190 -0.1404 0.0052 1.0000
11.750 1.7448 0.02952 0.02311 -0.1382 0.0051 1.0000
12.000 1.7544 0.03076 0.02443 -0.1361 0.0050 1.0000
12.250 1.7633 0.03209 0.02584 -0.1339 0.0049 1.0000
12.500 1.7716 0.03350 0.02733 -0.1318 0.0048 1.0000
12.750 1.7794 0.03498 0.02889 -0.1298 0.0046 1.0000
13.000 1.7865 0.03656 0.03055 -0.1278 0.0045 1.0000
13.250 1.7922 0.03832 0.03240 -0.1258 0.0044 1.0000
13.500 1.7970 0.04023 0.03439 -0.1239 0.0043 1.0000
13.750 1.8001 0.04236 0.03661 -0.1221 0.0042 1.0000
14.000 1.8023 0.04468 0.03903 -0.1203 0.0042 1.0000
14.250 1.8027 0.04730 0.04176 -0.1187 0.0041 1.0000
14.500 1.8016 0.05019 0.04476 -0.1173 0.0040 1.0000
14.750 1.7980 0.05351 0.04820 -0.1160 0.0040 1.0000
15.000 1.7910 0.05742 0.05225 -0.1149 0.0039 1.0000
15.250 1.7874 0.06108 0.05604 -0.1143 0.0038 1.0000
15.500 1.7870 0.06443 0.05950 -0.1140 0.0038 1.0000
15.750 1.7826 0.06847 0.06366 -0.1139 0.0038 1.0000
16.000 1.7782 0.07265 0.06796 -0.1140 0.0038 1.0000
16.250 1.7732 0.07710 0.07254 -0.1145 0.0037 1.0000
16.500 1.7654 0.08216 0.07773 -0.1154 0.0037 1.0000
16.750 1.7576 0.08737 0.08308 -0.1165 0.0037 1.0000
17.000 1.7490 0.09285 0.08869 -0.1180 0.0037 1.0000
17.250 1.7398 0.09861 0.09458 -0.1197 0.0036 1.0000
17.500 1.7278 0.10503 0.10114 -0.1220 0.0037 1.0000
17.750 1.7178 0.11122 0.10746 -0.1244 0.0036 1.0000
18.000 1.7057 0.11787 0.11425 -0.1273 0.0036 1.0000
18.250 1.6944 0.12450 0.12101 -0.1303 0.0036 1.0000
18.500 1.6835 0.13113 0.12778 -0.1336 0.0035 1.0000
18.750 1.6706 0.13827 0.13505 -0.1373 0.0035 1.0000
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Polar data table (+)
Polar graphs
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