EPPLER 377 (MODIFIED) AIRFOIL (e377m-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 377 (MODIFIED) AIRFOIL (e377m-il) Reynolds number: 500,000 Max Cl/Cd: 115.61 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e377m-il-500000-n5.txt Download as CSV file: xf-e377m-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 377 (MODIFIED) AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.2129 0.11600 0.11367 -0.0118 0.8459 0.0051
-10.250 -0.2064 0.11321 0.11077 -0.0125 0.8177 0.0051
-10.000 -0.1998 0.11042 0.10788 -0.0134 0.7932 0.0052
-9.750 -0.1926 0.10759 0.10497 -0.0145 0.7731 0.0052
-9.500 -0.1852 0.10474 0.10205 -0.0155 0.7552 0.0052
-9.250 -0.1778 0.10088 0.09811 -0.0160 0.7382 0.0054
-9.000 -0.1694 0.09831 0.09548 -0.0169 0.7226 0.0058
-8.750 -0.1615 0.09558 0.09269 -0.0178 0.7083 0.0060
-8.250 -0.1449 0.09008 0.08710 -0.0197 0.6836 0.0070
-8.000 -0.1366 0.08730 0.08429 -0.0206 0.6733 0.0072
-7.750 -0.1285 0.08458 0.08153 -0.0214 0.6632 0.0075
-7.500 -0.1202 0.08191 0.07883 -0.0223 0.6530 0.0077
-7.250 -0.1125 0.07937 0.07627 -0.0230 0.6440 0.0078
-7.000 -0.1052 0.07689 0.07377 -0.0237 0.6361 0.0079
-6.750 -0.0966 0.07430 0.07116 -0.0247 0.6284 0.0080
-6.500 -0.0856 0.07159 0.06842 -0.0263 0.6216 0.0080
-6.250 -0.0730 0.06875 0.06556 -0.0282 0.6144 0.0081
-6.000 -0.0594 0.06586 0.06262 -0.0303 0.6078 0.0081
-5.750 -0.0442 0.06288 0.05963 -0.0326 0.6014 0.0081
-5.500 -0.0287 0.05994 0.05666 -0.0349 0.5952 0.0081
-5.250 -0.0112 0.05687 0.05356 -0.0375 0.5899 0.0082
-5.000 0.0073 0.05376 0.05042 -0.0403 0.5839 0.0082
-4.750 0.0272 0.05061 0.04723 -0.0432 0.5786 0.0082
-4.500 0.0488 0.04733 0.04392 -0.0464 0.5736 0.0082
-4.250 0.0712 0.04408 0.04063 -0.0496 0.5686 0.0082
-4.000 0.0974 0.04083 0.03732 -0.0535 0.5642 0.0083
-3.750 0.1185 0.03727 0.03373 -0.0561 0.5595 0.0087
-3.500 0.1408 0.03539 0.03181 -0.0581 0.5539 0.0103
-3.250 0.1767 0.03318 0.02951 -0.0630 0.5494 0.0126
-3.000 0.2076 0.03037 0.02664 -0.0669 0.5452 0.0126
-2.750 0.2392 0.02759 0.02379 -0.0707 0.5406 0.0127
-2.500 0.2710 0.02493 0.02103 -0.0744 0.5364 0.0127
-2.250 0.3052 0.02236 0.01838 -0.0782 0.5322 0.0128
-1.750 0.3869 0.03669 0.03228 -0.0924 0.5311 0.0160
-1.500 0.4253 0.03506 0.03054 -0.0956 0.5265 0.0190
-1.250 0.4623 0.03336 0.02870 -0.0984 0.5222 0.0193
-1.000 0.4915 0.03079 0.02608 -0.1005 0.5179 0.0175
-0.750 0.5274 0.02865 0.02381 -0.1030 0.5134 0.0159
-0.500 0.5620 0.02688 0.02192 -0.1050 0.5095 0.0162
-0.250 0.5969 0.02531 0.02022 -0.1067 0.5055 0.0183
0.000 0.6298 0.02371 0.01850 -0.1082 0.5010 0.0175
0.250 0.6634 0.02207 0.01672 -0.1096 0.4968 0.0166
0.500 0.6976 0.02030 0.01476 -0.1108 0.4932 0.0160
0.750 0.7340 0.01793 0.01216 -0.1122 0.4893 0.0160
1.000 0.7748 0.01312 0.00659 -0.1141 0.4856 0.0176
1.250 0.8033 0.01228 0.00551 -0.1141 0.4813 0.0186
1.500 0.8311 0.01184 0.00494 -0.1140 0.4774 0.0196
1.750 0.8587 0.01172 0.00477 -0.1138 0.4731 0.0222
2.000 0.8861 0.01146 0.00444 -0.1136 0.4686 0.0249
2.250 0.9134 0.01094 0.00384 -0.1134 0.4646 0.0390
2.500 0.9406 0.01090 0.00387 -0.1132 0.4603 0.0581
2.750 0.9675 0.01100 0.00397 -0.1130 0.4557 0.0669
3.250 1.0212 0.01135 0.00434 -0.1125 0.4470 0.0777
3.500 1.0480 0.01133 0.00430 -0.1123 0.4420 0.0811
4.000 1.1014 0.01121 0.00414 -0.1118 0.4313 0.0881
4.250 1.1279 0.01129 0.00420 -0.1116 0.4249 0.0898
4.500 1.1544 0.01129 0.00421 -0.1113 0.4183 0.0924
4.750 1.1806 0.01117 0.00404 -0.1110 0.4114 0.0968
5.000 1.2068 0.01116 0.00406 -0.1108 0.4048 0.0983
5.250 1.2331 0.01125 0.00417 -0.1105 0.3976 0.0993
5.500 1.2592 0.01134 0.00429 -0.1103 0.3904 0.1005
5.750 1.2852 0.01147 0.00442 -0.1100 0.3819 0.1021
6.000 1.3111 0.01158 0.00459 -0.1098 0.3729 0.1045
6.250 1.3367 0.01169 0.00470 -0.1095 0.3632 0.1067
6.500 1.3620 0.01183 0.00483 -0.1091 0.3521 0.1084
6.750 1.3873 0.01200 0.00501 -0.1088 0.3393 0.1096
7.000 1.4122 0.01224 0.00525 -0.1085 0.3236 0.1109
7.250 1.4369 0.01253 0.00557 -0.1081 0.3063 0.1122
7.500 1.4608 0.01292 0.00592 -0.1077 0.2847 0.1137
7.750 1.4816 0.01375 0.00651 -0.1070 0.2377 0.1154
8.000 1.4979 0.01521 0.00752 -0.1060 0.1687 0.1176
8.250 1.5146 0.01652 0.00850 -0.1050 0.1172 0.1198
8.500 1.5329 0.01752 0.00931 -0.1041 0.0853 0.1212
8.750 1.5516 0.01838 0.01009 -0.1031 0.0646 0.1226
9.000 1.5671 0.01957 0.01116 -0.1019 0.0375 0.1240
9.250 1.5809 0.02084 0.01231 -0.1004 0.0170 0.1254
9.500 1.5924 0.02223 0.01365 -0.0985 0.0045 0.1269
9.750 1.6083 0.02306 0.01458 -0.0972 0.0034 0.1289
10.000 1.6224 0.02396 0.01560 -0.0956 0.0029 0.1308
10.250 1.6341 0.02495 0.01670 -0.0937 0.0026 0.1324
10.500 1.6406 0.02602 0.01790 -0.0911 0.0024 0.1342
10.750 1.6425 0.02730 0.01932 -0.0881 0.0022 0.1358
11.000 1.6417 0.02898 0.02115 -0.0854 0.0021 0.1373
11.250 1.6417 0.03088 0.02322 -0.0834 0.0020 0.1389
11.500 1.6430 0.03291 0.02537 -0.0820 0.0019 0.1406
11.750 1.6433 0.03524 0.02783 -0.0809 0.0019 0.1422
12.000 1.6433 0.03781 0.03052 -0.0801 0.0018 0.1434
12.250 1.6414 0.04076 0.03360 -0.0796 0.0017 0.1444
12.500 1.6390 0.04391 0.03688 -0.0793 0.0017 0.1457
12.750 1.6349 0.04739 0.04050 -0.0792 0.0016 0.1467
13.000 1.6299 0.05108 0.04433 -0.0792 0.0016 0.1482
13.250 1.6251 0.05485 0.04823 -0.0794 0.0016 0.1497
13.500 1.6187 0.05896 0.05247 -0.0798 0.0015 0.1509
13.750 1.6114 0.06327 0.05691 -0.0804 0.0015 0.1521
14.000 1.6044 0.06766 0.06143 -0.0811 0.0015 0.1535
14.250 1.5972 0.07226 0.06616 -0.0820 0.0015 0.1549
14.500 1.5892 0.07719 0.07122 -0.0832 0.0014 0.1563
14.750 1.5817 0.08217 0.07634 -0.0845 0.0014 0.1581
15.000 1.5746 0.08721 0.08152 -0.0859 0.0014 0.1600
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