EPPLER 377 AIRFOIL (e377-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 377 AIRFOIL (e377-il) Reynolds number: 1,000,000 Max Cl/Cd: 167.27 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e377-il-1000000.txt Download as CSV file: xf-e377-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 377 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.2817 0.14403 0.14257 0.0005 1.0000 0.0036
-12.500 -0.2742 0.14109 0.13964 -0.0009 1.0000 0.0036
-6.500 -0.1023 0.08451 0.08186 -0.0354 0.6642 0.0060
-6.000 -0.0768 0.07849 0.07579 -0.0383 0.6449 0.0062
-5.750 -0.0606 0.07612 0.07337 -0.0405 0.6365 0.0064
-5.500 -0.0432 0.07372 0.07095 -0.0429 0.6276 0.0065
-5.250 -0.0243 0.07127 0.06846 -0.0455 0.6198 0.0067
-5.000 -0.0042 0.06879 0.06594 -0.0483 0.6125 0.0069
-4.750 0.0175 0.06628 0.06340 -0.0514 0.6055 0.0072
-4.500 0.0406 0.06369 0.06077 -0.0546 0.5989 0.0076
-4.250 0.0656 0.06107 0.05811 -0.0581 0.5928 0.0082
-4.000 0.0947 0.05845 0.05545 -0.0622 0.5867 0.0087
-3.750 0.1267 0.05577 0.05271 -0.0671 0.5809 0.0088
-3.500 0.1591 0.05296 0.04986 -0.0718 0.5752 0.0089
-3.250 0.1932 0.05001 0.04683 -0.0766 0.5699 0.0089
-3.000 0.2220 0.04621 0.04298 -0.0805 0.5651 0.0093
-2.750 0.2502 0.04425 0.04098 -0.0832 0.5597 0.0099
-2.500 0.2827 0.04214 0.03880 -0.0867 0.5546 0.0109
-2.250 0.3204 0.03984 0.03643 -0.0909 0.5499 0.0124
-2.000 0.3625 0.03766 0.03416 -0.0958 0.5450 0.0129
-1.750 0.4003 0.03532 0.03173 -0.0997 0.5402 0.0130
-1.500 0.4391 0.03279 0.02912 -0.1035 0.5359 0.0130
0.750 0.7709 0.00998 0.00445 -0.1250 0.4982 0.0184
1.250 0.8276 0.00882 0.00292 -0.1248 0.4900 0.0188
1.500 0.8554 0.00841 0.00236 -0.1246 0.4856 0.0188
1.750 0.8830 0.00818 0.00202 -0.1243 0.4812 0.0193
2.000 0.9107 0.00794 0.00173 -0.1241 0.4772 0.0242
2.250 0.9381 0.00787 0.00169 -0.1238 0.4727 0.0436
2.500 0.9652 0.00795 0.00176 -0.1236 0.4679 0.0569
2.750 0.9926 0.00800 0.00183 -0.1234 0.4637 0.0631
3.000 1.0199 0.00799 0.00184 -0.1232 0.4587 0.0704
3.250 1.0469 0.00808 0.00189 -0.1229 0.4534 0.0761
3.500 1.0742 0.00808 0.00194 -0.1227 0.4482 0.0872
3.750 1.1012 0.00813 0.00199 -0.1225 0.4423 0.0985
4.000 1.1283 0.00819 0.00208 -0.1223 0.4368 0.1106
4.250 1.1554 0.00824 0.00215 -0.1221 0.4309 0.1227
4.500 1.1821 0.00835 0.00226 -0.1219 0.4250 0.1353
4.750 1.2092 0.00839 0.00235 -0.1217 0.4193 0.1506
5.000 1.2359 0.00850 0.00247 -0.1215 0.4127 0.1668
5.250 1.2628 0.00857 0.00261 -0.1213 0.4063 0.1848
5.500 1.2893 0.00869 0.00275 -0.1211 0.3989 0.2095
5.750 1.3160 0.00877 0.00290 -0.1209 0.3919 0.2409
6.000 1.3423 0.00891 0.00308 -0.1207 0.3835 0.2828
6.250 1.3699 0.00819 0.00336 -0.1210 0.3745 1.0000
6.500 1.3961 0.00837 0.00352 -0.1207 0.3654 1.0000
6.750 1.4220 0.00859 0.00370 -0.1205 0.3540 1.0000
7.000 1.4477 0.00883 0.00390 -0.1202 0.3401 1.0000
7.250 1.4725 0.00920 0.00417 -0.1198 0.3147 1.0000
7.500 1.4962 0.00975 0.00457 -0.1194 0.2790 1.0000
7.750 1.5175 0.01068 0.00518 -0.1188 0.2250 1.0000
8.000 1.5372 0.01184 0.00598 -0.1180 0.1677 1.0000
8.250 1.5580 0.01276 0.00668 -0.1174 0.1305 1.0000
8.750 1.5975 0.01473 0.00822 -0.1157 0.0650 1.0000
9.000 1.6123 0.01628 0.00948 -0.1144 0.0243 1.0000
9.250 1.6267 0.01777 0.01083 -0.1129 0.0045 1.0000
9.500 1.6467 0.01847 0.01162 -0.1119 0.0039 1.0000
9.750 1.6654 0.01926 0.01249 -0.1108 0.0035 1.0000
10.000 1.6827 0.02013 0.01344 -0.1095 0.0032 1.0000
10.250 1.6970 0.02123 0.01465 -0.1079 0.0029 1.0000
10.500 1.7083 0.02247 0.01605 -0.1060 0.0027 1.0000
10.750 1.7151 0.02392 0.01763 -0.1035 0.0027 1.0000
11.000 1.7187 0.02512 0.01893 -0.1004 0.0026 1.0000
11.250 1.7197 0.02645 0.02036 -0.0974 0.0026 1.0000
11.500 1.7200 0.02811 0.02212 -0.0951 0.0026 1.0000
11.750 1.7188 0.03022 0.02435 -0.0933 0.0025 1.0000
12.000 1.7200 0.03239 0.02662 -0.0921 0.0024 1.0000
12.250 1.7166 0.03529 0.02964 -0.0911 0.0024 1.0000
12.500 1.7137 0.03834 0.03281 -0.0905 0.0024 1.0000
12.750 1.7108 0.04153 0.03612 -0.0901 0.0023 1.0000
13.000 1.7058 0.04510 0.03981 -0.0899 0.0023 1.0000
13.250 1.7007 0.04879 0.04362 -0.0899 0.0022 1.0000
13.500 1.6937 0.05280 0.04775 -0.0899 0.0022 1.0000
13.750 1.6863 0.05699 0.05207 -0.0902 0.0021 1.0000
14.000 1.6790 0.06123 0.05642 -0.0906 0.0021 1.0000
14.250 1.6717 0.06559 0.06089 -0.0911 0.0020 1.0000
14.500 1.6628 0.07035 0.06577 -0.0919 0.0019 1.0000
14.750 1.6551 0.07513 0.07067 -0.0928 0.0019 1.0000
15.000 1.6471 0.08009 0.07575 -0.0940 0.0019 1.0000
15.250 1.6390 0.08520 0.08096 -0.0952 0.0018 1.0000
15.500 1.6308 0.09048 0.08636 -0.0967 0.0018 1.0000
15.750 1.6225 0.09589 0.09189 -0.0982 0.0017 1.0000
16.000 1.6139 0.10143 0.09756 -0.1000 0.0017 1.0000
16.250 1.6056 0.10709 0.10334 -0.1018 0.0017 1.0000
16.500 1.5972 0.11285 0.10923 -0.1039 0.0017 1.0000
16.750 1.5886 0.11873 0.11524 -0.1061 0.0017 1.0000
17.000 1.5798 0.12476 0.12140 -0.1085 0.0017 1.0000
17.250 1.5709 0.13096 0.12775 -0.1111 0.0017 1.0000
17.500 1.5619 0.13730 0.13423 -0.1140 0.0018 1.0000
17.750 1.5517 0.14398 0.14109 -0.1172 0.0018 1.0000
18.000 1.5398 0.15133 0.14862 -0.1210 0.0019 1.0000
18.250 1.5282 0.15885 0.15631 -0.1252 0.0019 1.0000
18.500 1.5162 0.16671 0.16434 -0.1298 0.0020 1.0000
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Polar data table (+)
Polar graphs
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