EPPLER 377 (MODIFIED) AIRFOIL (e377m-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 377 (MODIFIED) AIRFOIL (e377m-il) Reynolds number: 500,000 Max Cl/Cd: 117.67 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e377m-il-500000.txt Download as CSV file: xf-e377m-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-6.500 -0.0957 0.08424 0.08148 -0.0370 0.7548 0.0084
-6.250 -0.0837 0.08132 0.07848 -0.0379 0.7376 0.0086
-6.000 -0.0688 0.07889 0.07597 -0.0397 0.7223 0.0087
-5.500 -0.0343 0.07410 0.07105 -0.0441 0.6951 0.0092
-5.250 -0.0149 0.07166 0.06854 -0.0467 0.6829 0.0095
-5.000 0.0059 0.06919 0.06600 -0.0494 0.6721 0.0098
-4.750 0.0281 0.06665 0.06339 -0.0524 0.6631 0.0104
-1.750 0.3954 0.03672 0.03255 -0.0945 0.5810 0.0186
-1.500 0.4245 0.03511 0.03085 -0.0963 0.5760 0.0202
-1.250 0.4585 0.03343 0.02910 -0.0987 0.5705 0.0231
-1.000 0.5010 0.03265 0.02815 -0.1018 0.5653 0.0251
-0.750 0.5360 0.03113 0.02652 -0.1039 0.5603 0.0253
-0.500 0.5696 0.02786 0.02315 -0.1066 0.5555 0.0262
-0.250 0.5957 0.02648 0.02169 -0.1074 0.5509 0.0278
0.000 0.6264 0.02532 0.02045 -0.1085 0.5461 0.0309
0.250 0.6656 0.02513 0.02011 -0.1098 0.5409 0.0355
0.750 0.7262 0.02136 0.01611 -0.1122 0.5324 0.0377
1.000 0.7554 0.02040 0.01510 -0.1127 0.5275 0.0392
1.250 0.7859 0.01945 0.01402 -0.1132 0.5230 0.0413
1.500 0.8252 0.01657 0.01076 -0.1144 0.5193 0.0305
1.750 0.8637 0.01157 0.00492 -0.1156 0.5156 0.0332
2.000 0.8915 0.01101 0.00421 -0.1154 0.5109 0.0390
2.250 0.9186 0.01146 0.00475 -0.1150 0.5065 0.0613
2.500 0.9449 0.01251 0.00598 -0.1146 0.5018 0.0637
2.750 0.9715 0.01283 0.00632 -0.1144 0.4970 0.0723
3.000 0.9974 0.01329 0.00680 -0.1141 0.4925 0.0777
3.250 1.0244 0.01325 0.00676 -0.1140 0.4879 0.0851
3.500 1.0515 0.01309 0.00657 -0.1138 0.4830 0.0894
3.750 1.0790 0.01281 0.00617 -0.1135 0.4783 0.0953
4.000 1.1052 0.01288 0.00631 -0.1134 0.4729 0.1004
4.250 1.1322 0.01348 0.00686 -0.1129 0.4670 0.1174
4.500 1.1584 0.01286 0.00623 -0.1130 0.4617 0.1196
4.750 1.1851 0.01269 0.00611 -0.1129 0.4555 0.1229
5.000 1.2119 0.01274 0.00609 -0.1125 0.4499 0.1302
5.250 1.2382 0.01254 0.00597 -0.1124 0.4440 0.1341
5.500 1.2648 0.01255 0.00595 -0.1121 0.4377 0.1423
5.750 1.2909 0.01245 0.00589 -0.1119 0.4313 0.1453
6.000 1.3173 0.01256 0.00600 -0.1116 0.4241 0.1532
6.250 1.3431 0.01244 0.00595 -0.1114 0.4171 0.1557
6.500 1.3692 0.01252 0.00605 -0.1111 0.4090 0.1654
6.750 1.3949 0.01246 0.00607 -0.1109 0.4008 0.1719
7.250 1.4459 0.01264 0.00632 -0.1103 0.3813 0.2002
7.500 1.4719 0.01256 0.00624 -0.1097 0.3716 0.1392
7.750 1.4968 0.01272 0.00642 -0.1093 0.3574 0.1402
8.000 1.5205 0.01296 0.00663 -0.1089 0.3343 0.1433
8.250 1.5428 0.01345 0.00700 -0.1083 0.2967 0.1463
8.500 1.5623 0.01435 0.00762 -0.1075 0.2453 0.1479
8.750 1.5790 0.01560 0.00857 -0.1064 0.1898 0.1496
9.000 1.5964 0.01672 0.00946 -0.1054 0.1506 0.1513
9.250 1.6132 0.01781 0.01037 -0.1043 0.1168 0.1528
9.500 1.6277 0.01906 0.01142 -0.1030 0.0825 0.1547
9.750 1.6388 0.02058 0.01271 -0.1012 0.0486 0.1566
10.000 1.6423 0.02266 0.01452 -0.0986 0.0147 0.1584
10.250 1.6506 0.02406 0.01594 -0.0963 0.0080 0.1614
10.500 1.6589 0.02527 0.01726 -0.0940 0.0066 0.1641
10.750 1.6607 0.02650 0.01862 -0.0907 0.0058 0.1664
11.000 1.6588 0.02813 0.02041 -0.0875 0.0054 0.1681
11.250 1.6575 0.03002 0.02244 -0.0851 0.0052 0.1697
11.500 1.6568 0.03213 0.02470 -0.0834 0.0052 0.1716
11.750 1.6553 0.03459 0.02729 -0.0821 0.0050 0.1733
12.000 1.6530 0.03737 0.03022 -0.0811 0.0049 0.1752
12.250 1.6491 0.04055 0.03353 -0.0805 0.0046 0.1765
12.500 1.6446 0.04396 0.03708 -0.0802 0.0045 0.1782
12.750 1.6392 0.04761 0.04087 -0.0801 0.0045 0.1801
13.000 1.6325 0.05156 0.04495 -0.0801 0.0043 0.1820
13.250 1.6255 0.05564 0.04916 -0.0803 0.0042 0.1840
13.500 1.6176 0.05997 0.05362 -0.0807 0.0042 0.1859
13.750 1.6100 0.06432 0.05810 -0.0812 0.0041 0.1879
14.000 1.6020 0.06890 0.06281 -0.0819 0.0040 0.1904
14.250 1.5938 0.07367 0.06771 -0.0828 0.0040 0.1934
14.500 1.5867 0.07843 0.07259 -0.0837 0.0039 0.1968
14.750 1.5801 0.08319 0.07751 -0.0848 0.0039 0.2002
15.000 1.5741 0.08799 0.08244 -0.0859 0.0039 0.2042
15.250 1.5684 0.09283 0.08743 -0.0870 0.0039 0.2090
16.750 1.3177 0.13632 0.13255 -0.0975 0.0043 0.2121
17.000 1.3055 0.14147 0.13786 -0.0999 0.0042 0.2162
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Polar data table (+)
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