EPPLER 377 (MODIFIED) AIRFOIL (e377m-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 377 (MODIFIED) AIRFOIL (e377m-il) Reynolds number: 1,000,000 Max Cl/Cd: 136.98 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e377m-il-1000000-n5.txt Download as CSV file: xf-e377m-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.1759 0.09799 0.09515 -0.0246 0.6320 0.0049
-7.750 -0.1679 0.09576 0.09289 -0.0252 0.6231 0.0050
-7.500 -0.1602 0.09371 0.09083 -0.0258 0.6149 0.0050
-7.250 -0.1490 0.09142 0.08851 -0.0274 0.6065 0.0051
-7.000 -0.1362 0.08896 0.08604 -0.0293 0.6005 0.0051
-6.750 -0.1226 0.08645 0.08350 -0.0313 0.5929 0.0051
-6.500 -0.1078 0.08389 0.08093 -0.0335 0.5875 0.0051
-6.250 -0.0920 0.08133 0.07834 -0.0357 0.5806 0.0051
-6.000 -0.0750 0.07869 0.07568 -0.0383 0.5756 0.0051
-5.750 -0.0568 0.07598 0.07294 -0.0409 0.5700 0.0051
-5.500 -0.0377 0.07334 0.07027 -0.0436 0.5642 0.0051
-5.250 -0.0177 0.07056 0.06747 -0.0464 0.5594 0.0051
-5.000 0.0019 0.06801 0.06489 -0.0490 0.5544 0.0048
-4.750 0.0249 0.06532 0.06217 -0.0522 0.5497 0.0043
-4.500 0.0497 0.06248 0.05930 -0.0557 0.5451 0.0040
-4.250 0.0762 0.05957 0.05635 -0.0593 0.5401 0.0039
-4.000 0.1044 0.05665 0.05338 -0.0632 0.5359 0.0040
-3.750 0.1344 0.05365 0.05034 -0.0672 0.5318 0.0044
-3.500 0.1710 0.04959 0.04621 -0.0727 0.5278 0.0053
-3.000 0.2254 0.04642 0.04295 -0.0775 0.5188 0.0067
-2.750 0.2588 0.04382 0.04029 -0.0812 0.5147 0.0070
-2.500 0.2937 0.04114 0.03753 -0.0850 0.5106 0.0069
-2.250 0.3330 0.03797 0.03426 -0.0895 0.5069 0.0078
-2.000 0.3672 0.03578 0.03200 -0.0926 0.5028 0.0089
-1.750 0.3966 0.03452 0.03068 -0.0944 0.4983 0.0098
-1.500 0.4297 0.03279 0.02887 -0.0968 0.4945 0.0113
-1.250 0.4659 0.03049 0.02648 -0.0998 0.4909 0.0102
-1.000 0.5025 0.02823 0.02412 -0.1025 0.4867 0.0099
-0.750 0.5377 0.02628 0.02205 -0.1047 0.4824 0.0106
-0.500 0.5730 0.02435 0.02000 -0.1067 0.4789 0.0116
-0.250 0.6069 0.02262 0.01816 -0.1083 0.4753 0.0121
0.000 0.6395 0.02114 0.01658 -0.1095 0.4710 0.0125
0.250 0.6750 0.01893 0.01418 -0.1111 0.4669 0.0122
0.500 0.7221 0.01217 0.00660 -0.1144 0.4642 0.0123
0.750 0.7511 0.01105 0.00526 -0.1146 0.4604 0.0127
1.000 0.7792 0.01030 0.00432 -0.1146 0.4561 0.0134
1.250 0.8068 0.00993 0.00383 -0.1144 0.4517 0.0147
1.500 0.8344 0.00966 0.00349 -0.1142 0.4480 0.0156
1.750 0.8618 0.00942 0.00320 -0.1141 0.4439 0.0164
2.000 0.8889 0.00919 0.00290 -0.1139 0.4394 0.0178
2.250 0.9160 0.00893 0.00258 -0.1137 0.4354 0.0191
2.500 0.9427 0.00850 0.00214 -0.1135 0.4312 0.0281
2.750 0.9689 0.00818 0.00185 -0.1133 0.4264 0.0561
3.000 0.9958 0.00822 0.00191 -0.1131 0.4216 0.0720
3.250 1.0229 0.00828 0.00197 -0.1128 0.4160 0.0771
3.500 1.0498 0.00843 0.00211 -0.1126 0.4093 0.0822
3.750 1.0769 0.00853 0.00222 -0.1124 0.4028 0.0855
4.000 1.1036 0.00864 0.00230 -0.1122 0.3954 0.0879
4.250 1.1305 0.00872 0.00240 -0.1120 0.3889 0.0893
4.500 1.1572 0.00886 0.00252 -0.1118 0.3816 0.0909
4.750 1.1839 0.00893 0.00259 -0.1116 0.3748 0.0924
5.250 1.2368 0.00913 0.00278 -0.1111 0.3576 0.0954
5.500 1.2630 0.00927 0.00289 -0.1109 0.3482 0.0966
5.750 1.2891 0.00944 0.00304 -0.1107 0.3371 0.0974
6.000 1.3150 0.00960 0.00320 -0.1105 0.3246 0.0990
6.250 1.3407 0.00983 0.00340 -0.1102 0.3094 0.1002
6.500 1.3660 0.01012 0.00363 -0.1099 0.2904 0.1013
6.750 1.3909 0.01046 0.00390 -0.1096 0.2701 0.1025
7.000 1.4148 0.01095 0.00427 -0.1092 0.2412 0.1039
7.250 1.4354 0.01196 0.00494 -0.1086 0.1831 0.1052
7.500 1.4550 0.01309 0.00574 -0.1078 0.1253 0.1066
7.750 1.4758 0.01396 0.00640 -0.1071 0.0899 0.1078
8.000 1.4970 0.01471 0.00701 -0.1064 0.0642 0.1088
8.250 1.5177 0.01548 0.00766 -0.1057 0.0427 0.1102
8.500 1.5369 0.01641 0.00846 -0.1048 0.0203 0.1121
8.750 1.5538 0.01757 0.00953 -0.1035 0.0031 0.1133
9.000 1.5748 0.01815 0.01021 -0.1027 0.0020 0.1148
9.250 1.5960 0.01866 0.01079 -0.1020 0.0019 0.1164
9.500 1.6164 0.01922 0.01142 -0.1011 0.0017 0.1180
9.750 1.6359 0.01982 0.01209 -0.1002 0.0016 0.1196
10.000 1.6544 0.02048 0.01283 -0.0991 0.0015 0.1209
10.250 1.6714 0.02121 0.01365 -0.0978 0.0013 0.1224
10.500 1.6869 0.02202 0.01454 -0.0964 0.0012 0.1242
10.750 1.6997 0.02295 0.01559 -0.0946 0.0011 0.1259
11.000 1.7064 0.02410 0.01685 -0.0920 0.0010 0.1277
11.250 1.7026 0.02553 0.01842 -0.0880 0.0009 0.1289
11.500 1.6959 0.02747 0.02050 -0.0845 0.0008 0.1298
11.750 1.6965 0.02921 0.02234 -0.0824 0.0008 0.1312
12.000 1.6985 0.03109 0.02431 -0.0809 0.0008 0.1322
12.250 1.6979 0.03343 0.02677 -0.0797 0.0008 0.1329
12.500 1.6964 0.03607 0.02952 -0.0788 0.0008 0.1343
12.750 1.6948 0.03892 0.03249 -0.0782 0.0007 0.1353
13.000 1.6910 0.04217 0.03586 -0.0779 0.0007 0.1368
13.250 1.6880 0.04546 0.03927 -0.0778 0.0007 0.1381
13.500 1.6825 0.04919 0.04312 -0.0778 0.0007 0.1392
13.750 1.6767 0.05306 0.04711 -0.0780 0.0007 0.1402
14.000 1.6698 0.05720 0.05137 -0.0785 0.0007 0.1415
14.250 1.6629 0.06141 0.05569 -0.0790 0.0007 0.1425
14.500 1.6538 0.06612 0.06054 -0.0799 0.0007 0.1433
14.750 1.6459 0.07084 0.06540 -0.0809 0.0007 0.1441
15.000 1.6383 0.07568 0.07036 -0.0821 0.0007 0.1454
15.250 1.6293 0.08092 0.07573 -0.0835 0.0007 0.1468
15.500 1.6212 0.08615 0.08108 -0.0851 0.0007 0.1484
15.750 1.6124 0.09165 0.08671 -0.0869 0.0007 0.1500
16.000 1.6038 0.09728 0.09246 -0.0888 0.0007 0.1516
16.250 1.5948 0.10305 0.09837 -0.0909 0.0007 0.1532
16.500 1.5860 0.10896 0.10440 -0.0932 0.0007 0.1545
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