E64 (8.45%) (e64-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: E64 (8.45%) (e64-il) Reynolds number: 500,000 Max Cl/Cd: 103.33 at α=2.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e64-il-500000-n5.txt Download as CSV file: xf-e64-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4026 0.10334 0.10100 -0.0316 1.0000 0.0098
-9.500 -0.3996 0.10132 0.09900 -0.0311 1.0000 0.0101
-9.250 -0.4010 0.09791 0.09561 -0.0315 1.0000 0.0101
-9.000 -0.3973 0.09636 0.09408 -0.0308 1.0000 0.0106
-8.500 -0.4016 0.09092 0.08870 -0.0303 1.0000 0.0110
-8.000 -0.2834 0.05955 0.05744 -0.0518 0.9882 0.0089
-6.500 -0.2727 0.02391 0.01995 -0.1027 0.9612 0.0061
-6.250 -0.2460 0.02090 0.01647 -0.1043 0.9576 0.0061
-6.000 -0.2197 0.01846 0.01361 -0.1051 0.9531 0.0062
-5.750 -0.1898 0.01587 0.01060 -0.1065 0.9504 0.0064
-5.500 -0.1581 0.01449 0.00903 -0.1078 0.9483 0.0067
-5.250 -0.1258 0.01352 0.00792 -0.1090 0.9463 0.0070
-5.000 -0.0998 0.01278 0.00706 -0.1088 0.9405 0.0074
-4.750 -0.0689 0.01202 0.00619 -0.1096 0.9367 0.0077
-4.500 -0.0360 0.01139 0.00547 -0.1108 0.9339 0.0083
-4.250 -0.0070 0.01095 0.00497 -0.1111 0.9286 0.0090
-4.000 0.0234 0.01046 0.00439 -0.1117 0.9235 0.0093
-3.750 0.0559 0.00991 0.00377 -0.1127 0.9194 0.0095
-3.500 0.0845 0.00938 0.00314 -0.1129 0.9127 0.0102
-3.250 0.1153 0.00903 0.00271 -0.1135 0.9069 0.0111
-3.000 0.1448 0.00877 0.00238 -0.1138 0.9000 0.0124
-2.750 0.1746 0.00856 0.00211 -0.1141 0.8925 0.0144
-2.500 0.2032 0.00814 0.00185 -0.1144 0.8841 0.0562
-2.250 0.2324 0.00780 0.00167 -0.1148 0.8759 0.1142
-2.000 0.2602 0.00757 0.00155 -0.1149 0.8662 0.1597
-1.750 0.2883 0.00726 0.00146 -0.1151 0.8568 0.2390
-1.500 0.3162 0.00688 0.00140 -0.1154 0.8469 0.3511
-1.250 0.3438 0.00670 0.00135 -0.1153 0.8356 0.4157
-1.000 0.3713 0.00659 0.00131 -0.1153 0.8236 0.4642
-0.750 0.3987 0.00648 0.00129 -0.1151 0.8112 0.5144
-0.500 0.4258 0.00638 0.00129 -0.1149 0.7982 0.5690
-0.250 0.4526 0.00630 0.00130 -0.1146 0.7845 0.6200
0.000 0.4791 0.00626 0.00132 -0.1143 0.7697 0.6672
0.250 0.5050 0.00622 0.00135 -0.1137 0.7530 0.7143
0.500 0.5302 0.00621 0.00139 -0.1130 0.7353 0.7614
0.750 0.5545 0.00621 0.00145 -0.1121 0.7175 0.8072
1.000 0.5777 0.00621 0.00150 -0.1108 0.6988 0.8517
1.250 0.5991 0.00624 0.00154 -0.1091 0.6786 0.8976
1.500 0.6228 0.00627 0.00156 -0.1080 0.6567 0.9550
1.750 0.6523 0.00642 0.00159 -0.1083 0.6320 1.0000
2.000 0.6779 0.00661 0.00167 -0.1079 0.6065 1.0000
2.250 0.7033 0.00682 0.00178 -0.1074 0.5803 1.0000
2.500 0.7285 0.00705 0.00189 -0.1068 0.5530 1.0000
2.750 0.7534 0.00731 0.00202 -0.1063 0.5232 1.0000
3.000 0.7780 0.00760 0.00217 -0.1057 0.4911 1.0000
3.250 0.8023 0.00792 0.00236 -0.1051 0.4567 1.0000
3.500 0.8265 0.00826 0.00255 -0.1044 0.4210 1.0000
3.750 0.8511 0.00858 0.00275 -0.1039 0.3901 1.0000
4.000 0.8740 0.00906 0.00301 -0.1031 0.3423 1.0000
4.250 0.8949 0.00975 0.00336 -0.1020 0.2735 1.0000
4.500 0.9161 0.01045 0.00372 -0.1011 0.2093 1.0000
4.750 0.9383 0.01105 0.00408 -0.1002 0.1624 1.0000
5.000 0.9618 0.01152 0.00442 -0.0996 0.1340 1.0000
5.250 0.9845 0.01207 0.00481 -0.0989 0.1006 1.0000
5.500 1.0075 0.01259 0.00521 -0.0981 0.0754 1.0000
5.750 1.0300 0.01315 0.00564 -0.0973 0.0512 1.0000
6.000 1.0513 0.01384 0.00618 -0.0964 0.0261 1.0000
6.250 1.0730 0.01449 0.00675 -0.0954 0.0129 1.0000
6.500 1.0959 0.01499 0.00728 -0.0946 0.0107 1.0000
6.750 1.1191 0.01545 0.00781 -0.0938 0.0100 1.0000
7.000 1.1420 0.01592 0.00835 -0.0930 0.0096 1.0000
7.250 1.1643 0.01644 0.00894 -0.0921 0.0092 1.0000
7.500 1.1860 0.01701 0.00958 -0.0911 0.0088 1.0000
7.750 1.2071 0.01763 0.01030 -0.0901 0.0085 1.0000
8.000 1.2274 0.01831 0.01105 -0.0889 0.0082 1.0000
8.250 1.2467 0.01905 0.01188 -0.0876 0.0079 1.0000
8.500 1.2647 0.01989 0.01280 -0.0861 0.0076 1.0000
8.750 1.2813 0.02082 0.01382 -0.0844 0.0074 1.0000
9.000 1.2951 0.02197 0.01506 -0.0823 0.0071 1.0000
9.250 1.3050 0.02341 0.01663 -0.0796 0.0068 1.0000
9.500 1.3193 0.02428 0.01760 -0.0776 0.0067 1.0000
9.750 1.3317 0.02527 0.01870 -0.0753 0.0066 1.0000
10.000 1.3433 0.02633 0.01987 -0.0730 0.0065 1.0000
10.250 1.3536 0.02751 0.02117 -0.0706 0.0064 1.0000
10.500 1.3634 0.02875 0.02253 -0.0682 0.0063 1.0000
10.750 1.3722 0.03010 0.02402 -0.0659 0.0062 1.0000
11.000 1.3798 0.03159 0.02565 -0.0635 0.0061 1.0000
11.250 1.3865 0.03317 0.02739 -0.0612 0.0060 1.0000
11.500 1.3918 0.03491 0.02930 -0.0589 0.0059 1.0000
11.750 1.3959 0.03681 0.03136 -0.0567 0.0058 1.0000
12.000 1.3986 0.03886 0.03358 -0.0547 0.0057 1.0000
12.250 1.3994 0.04116 0.03607 -0.0527 0.0056 1.0000
12.500 1.3988 0.04367 0.03876 -0.0510 0.0056 1.0000
12.750 1.3965 0.04644 0.04171 -0.0495 0.0055 1.0000
13.000 1.3923 0.04955 0.04501 -0.0484 0.0054 1.0000
13.250 1.3867 0.05295 0.04860 -0.0476 0.0054 1.0000
13.500 1.3790 0.05679 0.05264 -0.0474 0.0053 1.0000
13.750 1.3698 0.06109 0.05713 -0.0477 0.0053 1.0000
14.000 1.3586 0.06595 0.06218 -0.0486 0.0052 1.0000
14.250 1.3458 0.07139 0.06782 -0.0502 0.0052 1.0000
14.500 1.3319 0.07742 0.07404 -0.0526 0.0052 1.0000
14.750 1.3164 0.08419 0.08100 -0.0558 0.0052 1.0000
15.000 1.2999 0.09170 0.08870 -0.0598 0.0052 1.0000
15.250 1.2819 0.10008 0.09726 -0.0647 0.0052 1.0000
15.500 1.2624 0.10934 0.10671 -0.0703 0.0052 1.0000
15.750 1.2411 0.11965 0.11720 -0.0767 0.0053 1.0000
16.000 1.2185 0.13097 0.12869 -0.0839 0.0053 1.0000
16.250 1.1933 0.14374 0.14163 -0.0919 0.0054 1.0000
16.500 1.1631 0.15906 0.15711 -0.1014 0.0055 1.0000
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Polar data table (+)
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