E64 (8.45%) (e64-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: E64 (8.45%) (e64-il) Reynolds number: 1,000,000 Max Cl/Cd: 140.66 at α=2.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e64-il-1000000.txt Download as CSV file: xf-e64-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4014 0.10244 0.10081 -0.0282 1.0000 0.0086
-9.250 -0.4030 0.09907 0.09746 -0.0285 1.0000 0.0091
-9.000 -0.4061 0.09564 0.09405 -0.0288 1.0000 0.0094
-8.750 -0.3108 0.07233 0.07085 -0.0421 0.9963 0.0101
-8.500 -0.3047 0.06769 0.06622 -0.0451 0.9954 0.0103
-8.250 -0.2972 0.06366 0.06219 -0.0479 0.9941 0.0105
-8.000 -0.2925 0.05897 0.05751 -0.0512 0.9919 0.0106
-7.750 -0.2871 0.05384 0.05238 -0.0555 0.9892 0.0107
-7.500 -0.2800 0.04841 0.04695 -0.0611 0.9866 0.0109
-7.250 -0.2701 0.04210 0.04065 -0.0699 0.9829 0.0111
-7.000 -0.2604 0.03125 0.02970 -0.0866 0.9768 0.0111
-6.750 -0.2415 0.02186 0.02005 -0.0978 0.9743 0.0114
-6.500 -0.2167 0.01534 0.01320 -0.1046 0.9729 0.0122
-6.250 -0.1933 0.01256 0.01006 -0.1060 0.9681 0.0137
-6.000 -0.1674 0.01024 0.00737 -0.1081 0.9645 0.0138
-5.250 -0.1030 0.01361 0.00916 -0.1147 0.9614 0.0101
-5.000 -0.0707 0.01170 0.00708 -0.1159 0.9598 0.0093
-4.750 -0.0441 0.01072 0.00597 -0.1156 0.9550 0.0094
-4.500 -0.0143 0.01015 0.00532 -0.1159 0.9510 0.0097
-4.250 0.0163 0.00894 0.00398 -0.1167 0.9477 0.0104
-4.000 0.0465 0.00838 0.00335 -0.1173 0.9435 0.0110
-3.750 0.0743 0.00797 0.00290 -0.1173 0.9373 0.0114
-3.500 0.1057 0.00764 0.00251 -0.1180 0.9326 0.0123
-3.250 0.1332 0.00737 0.00219 -0.1178 0.9252 0.0131
-3.000 0.1632 0.00711 0.00185 -0.1182 0.9190 0.0137
-2.750 0.1910 0.00685 0.00154 -0.1180 0.9111 0.0174
-2.500 0.2199 0.00634 0.00129 -0.1184 0.9041 0.0933
-2.250 0.2470 0.00602 0.00117 -0.1183 0.8953 0.1619
-2.000 0.2749 0.00572 0.00108 -0.1185 0.8870 0.2418
-1.750 0.3024 0.00548 0.00102 -0.1185 0.8775 0.3148
-1.500 0.3298 0.00525 0.00098 -0.1185 0.8676 0.3914
-1.250 0.3572 0.00506 0.00095 -0.1185 0.8578 0.4663
-1.000 0.3845 0.00490 0.00094 -0.1184 0.8472 0.5404
-0.750 0.4116 0.00480 0.00094 -0.1182 0.8354 0.5917
-0.500 0.4386 0.00472 0.00094 -0.1179 0.8229 0.6430
-0.250 0.4653 0.00465 0.00096 -0.1176 0.8096 0.6931
0.000 0.4917 0.00460 0.00098 -0.1172 0.7960 0.7445
0.250 0.5176 0.00456 0.00102 -0.1166 0.7818 0.7909
0.500 0.5428 0.00454 0.00106 -0.1159 0.7664 0.8341
0.750 0.5667 0.00454 0.00110 -0.1149 0.7497 0.8766
1.000 0.5883 0.00454 0.00113 -0.1132 0.7324 0.9216
1.250 0.6152 0.00453 0.00112 -0.1128 0.7133 0.9825
1.500 0.6431 0.00465 0.00115 -0.1128 0.6930 1.0000
1.750 0.6695 0.00479 0.00121 -0.1125 0.6724 1.0000
2.000 0.6957 0.00495 0.00127 -0.1121 0.6496 1.0000
2.250 0.7216 0.00513 0.00134 -0.1117 0.6248 1.0000
2.500 0.7472 0.00533 0.00144 -0.1112 0.5974 1.0000
2.750 0.7726 0.00555 0.00155 -0.1107 0.5673 1.0000
3.000 0.7980 0.00578 0.00166 -0.1103 0.5381 1.0000
3.250 0.8233 0.00603 0.00179 -0.1098 0.5079 1.0000
3.500 0.8477 0.00636 0.00196 -0.1092 0.4669 1.0000
3.750 0.8697 0.00690 0.00219 -0.1082 0.4008 1.0000
4.000 0.8923 0.00743 0.00243 -0.1074 0.3394 1.0000
4.250 0.9162 0.00785 0.00266 -0.1067 0.2970 1.0000
4.500 0.9400 0.00828 0.00292 -0.1061 0.2573 1.0000
4.750 0.9631 0.00878 0.00321 -0.1054 0.2121 1.0000
5.000 0.9864 0.00927 0.00351 -0.1047 0.1730 1.0000
5.250 1.0091 0.00981 0.00384 -0.1039 0.1337 1.0000
5.500 1.0314 0.01040 0.00423 -0.1030 0.0946 1.0000
5.750 1.0526 0.01112 0.00470 -0.1020 0.0519 1.0000
6.000 1.0724 0.01199 0.00532 -0.1007 0.0158 1.0000
6.250 1.0965 0.01240 0.00574 -0.1000 0.0126 1.0000
6.500 1.1204 0.01282 0.00620 -0.0993 0.0115 1.0000
6.750 1.1436 0.01330 0.00672 -0.0985 0.0106 1.0000
7.000 1.1654 0.01395 0.00747 -0.0974 0.0098 1.0000
7.250 1.1877 0.01451 0.00810 -0.0965 0.0095 1.0000
7.500 1.2101 0.01503 0.00868 -0.0956 0.0092 1.0000
7.750 1.2317 0.01562 0.00933 -0.0945 0.0088 1.0000
8.000 1.2522 0.01630 0.01008 -0.0933 0.0085 1.0000
8.250 1.2721 0.01702 0.01087 -0.0920 0.0083 1.0000
8.500 1.2910 0.01781 0.01174 -0.0906 0.0082 1.0000
8.750 1.3091 0.01864 0.01266 -0.0890 0.0080 1.0000
9.000 1.3263 0.01954 0.01364 -0.0873 0.0078 1.0000
9.250 1.3428 0.02047 0.01465 -0.0856 0.0076 1.0000
9.500 1.3582 0.02147 0.01573 -0.0837 0.0074 1.0000
9.750 1.3718 0.02261 0.01695 -0.0816 0.0073 1.0000
10.000 1.3822 0.02391 0.01834 -0.0790 0.0071 1.0000
10.250 1.3899 0.02562 0.02016 -0.0760 0.0069 1.0000
10.500 1.3967 0.02793 0.02262 -0.0732 0.0068 1.0000
10.750 1.4020 0.03136 0.02631 -0.0705 0.0066 1.0000
11.000 1.4106 0.03159 0.02664 -0.0677 0.0064 1.0000
11.250 1.4178 0.03279 0.02799 -0.0651 0.0063 1.0000
11.500 1.4225 0.03445 0.02981 -0.0624 0.0062 1.0000
11.750 1.4247 0.03643 0.03195 -0.0597 0.0062 1.0000
12.000 1.4244 0.03866 0.03437 -0.0570 0.0061 1.0000
12.250 1.4216 0.04119 0.03708 -0.0544 0.0061 1.0000
12.500 1.4170 0.04391 0.03999 -0.0521 0.0060 1.0000
12.750 1.4095 0.04706 0.04333 -0.0501 0.0060 1.0000
13.000 1.3991 0.05070 0.04718 -0.0486 0.0060 1.0000
13.250 1.3879 0.05460 0.05127 -0.0477 0.0060 1.0000
13.500 1.3737 0.05919 0.05605 -0.0474 0.0060 1.0000
13.750 1.3588 0.06419 0.06124 -0.0480 0.0060 1.0000
14.000 1.3411 0.07006 0.06730 -0.0496 0.0060 1.0000
14.250 1.3235 0.07642 0.07384 -0.0520 0.0060 1.0000
14.500 1.3034 0.08383 0.08143 -0.0556 0.0060 1.0000
14.750 1.2830 0.09206 0.08983 -0.0601 0.0061 1.0000
15.000 1.2621 0.10111 0.09904 -0.0656 0.0061 1.0000
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Polar data table (+)
Polar graphs
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