EPPLER 376 AIRFOIL (e376-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 376 AIRFOIL (e376-il) Reynolds number: 200,000 Max Cl/Cd: 92.65 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e376-il-200000.txt Download as CSV file: xf-e376-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 376 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.1709 0.09802 0.09517 -0.0174 1.0000 0.0097
-8.500 -0.1632 0.09591 0.09312 -0.0187 1.0000 0.0097
-8.250 -0.1562 0.09400 0.09129 -0.0200 1.0000 0.0097
-8.000 -0.1453 0.09189 0.08924 -0.0228 0.9855 0.0098
-3.250 0.2084 0.05377 0.04948 -0.0774 0.7046 0.0154
-3.000 0.2297 0.05058 0.04620 -0.0790 0.6972 0.0159
-2.750 0.2580 0.04814 0.04370 -0.0819 0.6885 0.0167
-2.500 0.2891 0.04597 0.04140 -0.0850 0.6809 0.0176
-2.250 0.3221 0.04388 0.03921 -0.0883 0.6733 0.0188
-2.000 0.3569 0.04195 0.03717 -0.0916 0.6664 0.0205
-1.750 0.4149 0.04351 0.03844 -0.0974 0.6584 0.0228
-1.500 0.4497 0.04127 0.03608 -0.1003 0.6520 0.0231
-1.250 0.4665 0.03665 0.03148 -0.1012 0.6458 0.0242
-1.000 0.4954 0.03464 0.02933 -0.1031 0.6402 0.0255
-0.750 0.5278 0.03304 0.02767 -0.1052 0.6332 0.0272
-0.500 0.5611 0.03167 0.02612 -0.1071 0.6278 0.0292
-0.250 0.5965 0.03070 0.02506 -0.1090 0.6214 0.0318
0.000 0.6385 0.03145 0.02555 -0.1106 0.6156 0.0333
0.250 0.6720 0.02979 0.02375 -0.1122 0.6101 0.0338
0.500 0.6960 0.02675 0.02071 -0.1136 0.6043 0.0358
0.750 0.7258 0.02554 0.01936 -0.1145 0.5995 0.0387
1.000 0.7584 0.02478 0.01850 -0.1154 0.5938 0.0433
1.250 0.7931 0.02410 0.01762 -0.1161 0.5883 0.0470
1.500 0.8203 0.02279 0.01620 -0.1168 0.5838 0.0525
1.750 0.8560 0.02364 0.01683 -0.1165 0.5777 0.0581
2.000 0.8824 0.02133 0.01449 -0.1176 0.5729 0.0610
2.250 0.9111 0.02069 0.01374 -0.1178 0.5681 0.0664
2.500 0.9420 0.02026 0.01318 -0.1178 0.5624 0.0722
2.750 0.9697 0.01952 0.01233 -0.1180 0.5578 0.0773
3.000 0.9993 0.01914 0.01184 -0.1178 0.5527 0.0851
3.250 1.0274 0.01853 0.01117 -0.1178 0.5472 0.0887
3.500 1.0550 0.01818 0.01067 -0.1177 0.5429 0.1135
3.750 1.0874 0.01652 0.00860 -0.1169 0.5381 0.0548
4.000 1.1147 0.01604 0.00798 -0.1165 0.5327 0.0718
4.250 1.1408 0.01641 0.00835 -0.1163 0.5282 0.1140
4.500 1.1672 0.01632 0.00827 -0.1160 0.5221 0.1227
4.750 1.1936 0.01628 0.00821 -0.1157 0.5166 0.1328
5.000 1.2202 0.01632 0.00830 -0.1155 0.5111 0.1483
5.250 1.2461 0.01632 0.00836 -0.1151 0.5042 0.1697
5.500 1.2726 0.01637 0.00831 -0.1148 0.4991 0.1967
5.750 1.2983 0.01644 0.00854 -0.1146 0.4917 0.2382
6.000 1.3265 0.01575 0.00856 -0.1147 0.4859 1.0000
6.250 1.3517 0.01593 0.00887 -0.1143 0.4777 1.0000
6.500 1.3776 0.01607 0.00890 -0.1138 0.4713 1.0000
6.750 1.4024 0.01623 0.00921 -0.1134 0.4625 1.0000
7.000 1.4277 0.01637 0.00935 -0.1129 0.4550 1.0000
7.250 1.4526 0.01647 0.00954 -0.1124 0.4457 1.0000
7.500 1.4771 0.01660 0.00979 -0.1119 0.4357 1.0000
7.750 1.5017 0.01672 0.01005 -0.1113 0.4256 1.0000
8.000 1.5259 0.01683 0.01023 -0.1107 0.4143 1.0000
8.250 1.5494 0.01693 0.01047 -0.1100 0.3996 1.0000
8.500 1.5714 0.01696 0.01057 -0.1091 0.3740 1.0000
8.750 1.5925 0.01724 0.01089 -0.1082 0.3417 1.0000
9.000 1.6099 0.01798 0.01149 -0.1070 0.2898 1.0000
9.250 1.6229 0.01940 0.01258 -0.1056 0.2272 1.0000
9.500 1.6307 0.02142 0.01421 -0.1038 0.1671 1.0000
9.750 1.6350 0.02370 0.01613 -0.1018 0.1124 1.0000
10.000 1.6302 0.02663 0.01861 -0.0988 0.0546 1.0000
10.250 1.6178 0.02966 0.02140 -0.0948 0.0269 1.0000
10.500 1.6066 0.03236 0.02416 -0.0913 0.0214 1.0000
10.750 1.6011 0.03502 0.02701 -0.0892 0.0195 1.0000
11.000 1.5963 0.03797 0.03015 -0.0879 0.0182 1.0000
11.250 1.5913 0.04119 0.03355 -0.0870 0.0171 1.0000
11.500 1.5858 0.04468 0.03718 -0.0865 0.0159 1.0000
11.750 1.5781 0.04859 0.04121 -0.0862 0.0148 1.0000
12.000 1.5671 0.05304 0.04580 -0.0861 0.0140 1.0000
12.250 1.5555 0.05766 0.05059 -0.0860 0.0135 1.0000
12.500 1.5476 0.06184 0.05489 -0.0857 0.0131 1.0000
12.750 1.5443 0.06545 0.05864 -0.0854 0.0129 1.0000
13.000 1.5419 0.06896 0.06230 -0.0848 0.0126 1.0000
13.250 1.5409 0.07235 0.06584 -0.0841 0.0124 1.0000
13.500 1.5413 0.07564 0.06928 -0.0833 0.0122 1.0000
13.750 1.5425 0.07899 0.07281 -0.0824 0.0120 1.0000
14.000 1.5431 0.08263 0.07666 -0.0817 0.0120 1.0000
14.250 1.5417 0.08674 0.08100 -0.0813 0.0120 1.0000
14.500 1.5378 0.09142 0.08592 -0.0815 0.0120 1.0000
14.750 1.5308 0.09665 0.09141 -0.0824 0.0121 1.0000
15.000 1.5216 0.10239 0.09740 -0.0839 0.0122 1.0000
15.250 1.5105 0.10857 0.10382 -0.0860 0.0123 1.0000
15.500 1.4981 0.11513 0.11062 -0.0886 0.0124 1.0000
15.750 1.4850 0.12203 0.11775 -0.0918 0.0125 1.0000
16.000 1.4712 0.12929 0.12522 -0.0955 0.0126 1.0000
16.250 1.4572 0.13695 0.13309 -0.0999 0.0127 1.0000
16.500 1.4428 0.14499 0.14131 -0.1047 0.0128 1.0000
16.750 1.4287 0.15326 0.14977 -0.1099 0.0129 1.0000
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Polar data table (+)
Polar graphs
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