E64 (8.45%) (e64-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: E64 (8.45%) (e64-il) Reynolds number: 1,000,000 Max Cl/Cd: 113.24 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e64-il-1000000-n5.txt Download as CSV file: xf-e64-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E64 (8.45%)
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 -0.4056 0.10731 0.10563 -0.0278 1.0000 0.0052
-9.750 -0.4055 0.10390 0.10224 -0.0282 1.0000 0.0054
-9.500 -0.4029 0.10033 0.09868 -0.0295 0.9998 0.0054
-9.250 -0.3948 0.09578 0.09413 -0.0330 0.9990 0.0051
-9.000 -0.3855 0.09129 0.08964 -0.0368 0.9978 0.0052
-8.750 -0.3759 0.08609 0.08444 -0.0414 0.9964 0.0058
-8.500 -0.3671 0.08169 0.08006 -0.0457 0.9947 0.0052
-8.250 -0.3596 0.07686 0.07524 -0.0502 0.9919 0.0052
-8.000 -0.3506 0.07157 0.06995 -0.0560 0.9883 0.0053
-7.750 -0.3357 0.06508 0.06347 -0.0653 0.9850 0.0053
-7.500 -0.3514 0.02128 0.01816 -0.1082 0.9651 0.0040
-7.250 -0.3241 0.01814 0.01456 -0.1102 0.9622 0.0040
-7.000 -0.2943 0.01607 0.01218 -0.1119 0.9601 0.0041
-6.750 -0.2701 0.01472 0.01061 -0.1118 0.9545 0.0041
-6.500 -0.2411 0.01359 0.00929 -0.1126 0.9507 0.0042
-6.250 -0.2102 0.01264 0.00818 -0.1137 0.9477 0.0043
-6.000 -0.1818 0.01188 0.00729 -0.1141 0.9430 0.0045
-5.750 -0.1527 0.01122 0.00652 -0.1146 0.9377 0.0047
-5.500 -0.1221 0.01058 0.00577 -0.1153 0.9331 0.0050
-5.250 -0.0943 0.01005 0.00514 -0.1155 0.9265 0.0053
-5.000 -0.0650 0.00959 0.00458 -0.1159 0.9202 0.0056
-4.750 -0.0369 0.00916 0.00408 -0.1160 0.9133 0.0058
-4.500 -0.0085 0.00882 0.00365 -0.1162 0.9060 0.0059
-4.250 0.0194 0.00851 0.00328 -0.1162 0.8985 0.0061
-3.750 0.0748 0.00775 0.00236 -0.1162 0.8817 0.0071
-3.500 0.1026 0.00752 0.00206 -0.1162 0.8725 0.0075
-3.250 0.1302 0.00734 0.00180 -0.1161 0.8624 0.0079
-3.000 0.1578 0.00719 0.00158 -0.1160 0.8519 0.0086
-2.750 0.1854 0.00707 0.00140 -0.1159 0.8417 0.0093
-2.500 0.2128 0.00698 0.00123 -0.1157 0.8311 0.0107
-2.000 0.2672 0.00655 0.00096 -0.1155 0.8070 0.0766
-1.750 0.2943 0.00640 0.00088 -0.1154 0.7938 0.1182
-1.500 0.3213 0.00623 0.00082 -0.1153 0.7802 0.1733
-1.250 0.3483 0.00610 0.00078 -0.1152 0.7662 0.2241
-1.000 0.3750 0.00585 0.00076 -0.1152 0.7514 0.3222
-0.750 0.4018 0.00577 0.00076 -0.1150 0.7352 0.3751
-0.500 0.4283 0.00575 0.00076 -0.1148 0.7173 0.4156
-0.250 0.4549 0.00573 0.00077 -0.1145 0.6979 0.4570
0.000 0.4814 0.00572 0.00080 -0.1143 0.6788 0.5052
0.250 0.5079 0.00573 0.00084 -0.1140 0.6594 0.5479
0.500 0.5343 0.00575 0.00090 -0.1137 0.6383 0.5886
0.750 0.5603 0.00580 0.00096 -0.1134 0.6145 0.6303
1.000 0.5862 0.00587 0.00104 -0.1130 0.5897 0.6740
1.250 0.6120 0.00594 0.00113 -0.1126 0.5638 0.7172
1.500 0.6376 0.00603 0.00123 -0.1121 0.5381 0.7586
1.750 0.6628 0.00613 0.00134 -0.1116 0.5129 0.7982
2.000 0.6872 0.00624 0.00146 -0.1108 0.4854 0.8401
2.250 0.7100 0.00636 0.00159 -0.1097 0.4565 0.8851
2.500 0.7301 0.00647 0.00169 -0.1079 0.4272 0.9371
2.750 0.7576 0.00669 0.00179 -0.1079 0.3914 1.0000
3.000 0.7831 0.00697 0.00194 -0.1075 0.3611 1.0000
3.250 0.8087 0.00725 0.00210 -0.1071 0.3319 1.0000
3.500 0.8311 0.00783 0.00236 -0.1063 0.2656 1.0000
3.750 0.8531 0.00847 0.00266 -0.1054 0.1975 1.0000
4.000 0.8767 0.00896 0.00292 -0.1048 0.1530 1.0000
4.250 0.9014 0.00933 0.00317 -0.1043 0.1266 1.0000
4.500 0.9259 0.00972 0.00343 -0.1038 0.1008 1.0000
4.750 0.9502 0.01012 0.00371 -0.1033 0.0771 1.0000
5.000 0.9735 0.01064 0.00406 -0.1026 0.0475 1.0000
5.250 0.9969 0.01113 0.00444 -0.1019 0.0260 1.0000
5.500 1.0202 0.01165 0.00486 -0.1011 0.0100 1.0000
5.750 1.0451 0.01195 0.00518 -0.1006 0.0087 1.0000
6.000 1.0699 0.01228 0.00552 -0.1001 0.0080 1.0000
6.250 1.0943 0.01263 0.00591 -0.0996 0.0074 1.0000
6.500 1.1183 0.01303 0.00636 -0.0989 0.0069 1.0000
6.750 1.1422 0.01342 0.00679 -0.0983 0.0067 1.0000
7.000 1.1660 0.01381 0.00721 -0.0976 0.0066 1.0000
7.250 1.1894 0.01422 0.00767 -0.0969 0.0064 1.0000
7.500 1.2124 0.01468 0.00818 -0.0961 0.0062 1.0000
7.750 1.2349 0.01517 0.00873 -0.0953 0.0060 1.0000
8.000 1.2570 0.01568 0.00929 -0.0944 0.0058 1.0000
8.250 1.2788 0.01619 0.00985 -0.0935 0.0055 1.0000
8.500 1.3000 0.01676 0.01047 -0.0925 0.0053 1.0000
8.750 1.3204 0.01738 0.01114 -0.0913 0.0051 1.0000
9.000 1.3403 0.01802 0.01186 -0.0901 0.0050 1.0000
9.250 1.3594 0.01870 0.01261 -0.0888 0.0049 1.0000
9.500 1.3772 0.01948 0.01346 -0.0873 0.0047 1.0000
9.750 1.3936 0.02033 0.01439 -0.0856 0.0046 1.0000
10.000 1.4077 0.02133 0.01548 -0.0836 0.0045 1.0000
10.250 1.4176 0.02248 0.01674 -0.0808 0.0044 1.0000
10.500 1.4223 0.02393 0.01831 -0.0773 0.0043 1.0000
10.750 1.4316 0.02500 0.01949 -0.0746 0.0042 1.0000
11.000 1.4421 0.02596 0.02056 -0.0722 0.0042 1.0000
11.250 1.4522 0.02696 0.02165 -0.0698 0.0042 1.0000
11.500 1.4605 0.02812 0.02292 -0.0674 0.0041 1.0000
11.750 1.4679 0.02938 0.02428 -0.0650 0.0041 1.0000
12.000 1.4752 0.03065 0.02567 -0.0628 0.0040 1.0000
12.250 1.4797 0.03223 0.02737 -0.0604 0.0040 1.0000
12.500 1.4835 0.03391 0.02918 -0.0582 0.0039 1.0000
12.750 1.4866 0.03571 0.03111 -0.0561 0.0039 1.0000
13.000 1.4872 0.03784 0.03339 -0.0542 0.0038 1.0000
13.250 1.4876 0.04006 0.03575 -0.0525 0.0038 1.0000
13.500 1.4861 0.04261 0.03844 -0.0511 0.0037 1.0000
13.750 1.4835 0.04540 0.04137 -0.0499 0.0037 1.0000
14.000 1.4808 0.04835 0.04446 -0.0492 0.0036 1.0000
14.250 1.4753 0.05184 0.04810 -0.0489 0.0035 1.0000
14.500 1.4698 0.05552 0.05192 -0.0490 0.0035 1.0000
14.750 1.4626 0.05969 0.05624 -0.0496 0.0034 1.0000
15.000 1.4530 0.06449 0.06120 -0.0508 0.0034 1.0000
15.250 1.4424 0.06980 0.06665 -0.0526 0.0034 1.0000
15.500 1.4296 0.07587 0.07288 -0.0551 0.0033 1.0000
15.750 1.4153 0.08261 0.07978 -0.0583 0.0033 1.0000
16.000 1.3996 0.09004 0.08737 -0.0622 0.0033 1.0000
16.250 1.3818 0.09835 0.09584 -0.0667 0.0033 1.0000
16.500 1.3629 0.10728 0.10493 -0.0719 0.0033 1.0000
16.750 1.3418 0.11712 0.11493 -0.0777 0.0033 1.0000
17.000 1.3207 0.12734 0.12530 -0.0838 0.0033 1.0000
17.250 1.2996 0.13789 0.13599 -0.0903 0.0033 1.0000
17.500 1.2769 0.14928 0.14751 -0.0973 0.0034 1.0000
17.750 1.2547 0.16097 0.15933 -0.1045 0.0034 1.0000
18.000 1.2306 0.17384 0.17233 -0.1125 0.0034 1.0000
18.250 1.1978 0.19058 0.18920 -0.1226 0.0035 1.0000
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Polar data table (+)
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