EPPLER 377 AIRFOIL (e377-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 377 AIRFOIL (e377-il) Reynolds number: 1,000,000 Max Cl/Cd: 140.98 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e377-il-1000000-n5.txt Download as CSV file: xf-e377-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.1679 0.09596 0.09304 -0.0252 0.6181 0.0032
-7.500 -0.1595 0.09361 0.09067 -0.0262 0.6111 0.0031
-7.250 -0.1521 0.09112 0.08818 -0.0267 0.6045 0.0032
-6.750 -0.1314 0.08673 0.08377 -0.0292 0.5917 0.0039
-6.500 -0.1175 0.08470 0.08171 -0.0308 0.5853 0.0054
-6.250 -0.1024 0.08205 0.07906 -0.0331 0.5798 0.0056
-6.000 -0.0869 0.07947 0.07646 -0.0355 0.5736 0.0056
-5.750 -0.0693 0.07691 0.07387 -0.0382 0.5690 0.0056
-5.500 -0.0501 0.07427 0.07122 -0.0413 0.5635 0.0057
-5.250 -0.0302 0.07159 0.06851 -0.0443 0.5584 0.0057
-4.750 0.0115 0.06593 0.06279 -0.0504 0.5492 0.0056
-4.500 0.0324 0.06333 0.06017 -0.0531 0.5446 0.0053
-4.250 0.0574 0.06061 0.05741 -0.0567 0.5403 0.0049
-4.000 0.0849 0.05764 0.05441 -0.0608 0.5358 0.0047
-3.750 0.1143 0.05465 0.05138 -0.0651 0.5312 0.0046
-3.500 0.1457 0.05160 0.04827 -0.0696 0.5271 0.0048
-3.250 0.1866 0.04716 0.04377 -0.0766 0.5237 0.0059
-3.000 0.2147 0.04549 0.04206 -0.0792 0.5191 0.0062
-2.750 0.2447 0.04380 0.04031 -0.0821 0.5145 0.0071
-2.500 0.2803 0.04126 0.03770 -0.0863 0.5105 0.0079
-2.250 0.3183 0.03844 0.03481 -0.0909 0.5066 0.0077
-2.000 0.3598 0.03535 0.03163 -0.0959 0.5024 0.0083
-1.750 0.4037 0.03220 0.02835 -0.1012 0.4984 0.0096
-1.500 0.4323 0.03117 0.02728 -0.1027 0.4943 0.0104
-1.250 0.4651 0.02986 0.02590 -0.1049 0.4900 0.0128
-1.000 0.5044 0.02736 0.02328 -0.1084 0.4860 0.0112
-0.750 0.5535 0.02328 0.01898 -0.1135 0.4826 0.0099
-0.500 0.5896 0.02134 0.01692 -0.1157 0.4784 0.0103
-0.250 0.6245 0.01962 0.01507 -0.1175 0.4743 0.0112
0.000 0.6799 0.01079 0.00531 -0.1232 0.4717 0.0119
0.250 0.7088 0.00989 0.00416 -0.1233 0.4680 0.0123
0.500 0.7370 0.00935 0.00344 -0.1233 0.4636 0.0127
0.750 0.7651 0.00888 0.00278 -0.1231 0.4593 0.0126
1.000 0.7928 0.00858 0.00235 -0.1229 0.4555 0.0127
1.250 0.8206 0.00836 0.00205 -0.1227 0.4516 0.0128
1.500 0.8481 0.00822 0.00184 -0.1225 0.4470 0.0131
1.750 0.8755 0.00815 0.00171 -0.1222 0.4427 0.0137
2.000 0.9030 0.00811 0.00164 -0.1220 0.4389 0.0144
2.250 0.9304 0.00806 0.00154 -0.1218 0.4343 0.0173
2.500 0.9577 0.00807 0.00153 -0.1215 0.4297 0.0212
2.750 0.9849 0.00804 0.00158 -0.1213 0.4254 0.0428
3.000 1.0121 0.00808 0.00163 -0.1211 0.4198 0.0532
3.250 1.0391 0.00815 0.00169 -0.1209 0.4138 0.0601
3.500 1.0663 0.00819 0.00176 -0.1207 0.4074 0.0708
4.000 1.1202 0.00835 0.00193 -0.1203 0.3934 0.0909
4.500 1.1739 0.00854 0.00213 -0.1199 0.3795 0.1087
4.750 1.2006 0.00867 0.00226 -0.1196 0.3717 0.1190
5.000 1.2273 0.00878 0.00240 -0.1194 0.3629 0.1302
5.250 1.2538 0.00892 0.00255 -0.1192 0.3537 0.1458
5.500 1.2801 0.00908 0.00272 -0.1190 0.3433 0.1635
5.750 1.3063 0.00927 0.00291 -0.1188 0.3307 0.1790
6.000 1.3323 0.00948 0.00311 -0.1185 0.3171 0.1994
6.250 1.3581 0.00974 0.00337 -0.1183 0.3008 0.2210
6.500 1.3832 0.01009 0.00366 -0.1180 0.2776 0.2447
6.750 1.4061 0.01081 0.00417 -0.1176 0.2305 0.2804
7.000 1.4287 0.01144 0.00480 -0.1172 0.1884 0.5207
7.500 1.4722 0.01261 0.00615 -0.1162 0.1028 1.0000
7.750 1.4927 0.01359 0.00689 -0.1155 0.0657 1.0000
8.000 1.5141 0.01435 0.00752 -0.1148 0.0441 1.0000
8.250 1.5334 0.01539 0.00839 -0.1139 0.0183 1.0000
8.500 1.5523 0.01642 0.00932 -0.1129 0.0033 1.0000
8.750 1.5744 0.01695 0.00990 -0.1122 0.0025 1.0000
9.000 1.5957 0.01755 0.01059 -0.1114 0.0021 1.0000
9.250 1.6160 0.01824 0.01136 -0.1105 0.0017 1.0000
9.500 1.6362 0.01887 0.01205 -0.1096 0.0015 1.0000
9.750 1.6559 0.01951 0.01275 -0.1087 0.0014 1.0000
10.000 1.6743 0.02024 0.01355 -0.1076 0.0014 1.0000
10.250 1.6913 0.02104 0.01443 -0.1064 0.0013 1.0000
10.500 1.7071 0.02188 0.01535 -0.1050 0.0012 1.0000
10.750 1.7205 0.02285 0.01642 -0.1033 0.0012 1.0000
11.000 1.7318 0.02386 0.01752 -0.1015 0.0011 1.0000
11.250 1.7371 0.02491 0.01866 -0.0986 0.0010 1.0000
11.500 1.7390 0.02617 0.02001 -0.0957 0.0010 1.0000
11.750 1.7397 0.02777 0.02171 -0.0934 0.0009 1.0000
12.000 1.7410 0.02960 0.02364 -0.0916 0.0009 1.0000
12.250 1.7419 0.03174 0.02587 -0.0904 0.0008 1.0000
12.500 1.7414 0.03426 0.02850 -0.0894 0.0008 1.0000
12.750 1.7404 0.03700 0.03135 -0.0888 0.0008 1.0000
13.000 1.7375 0.04011 0.03458 -0.0883 0.0007 1.0000
13.250 1.7312 0.04379 0.03838 -0.0881 0.0007 1.0000
13.500 1.7221 0.04797 0.04269 -0.0882 0.0006 1.0000
13.750 1.7063 0.05317 0.04806 -0.0885 0.0006 1.0000
14.000 1.6938 0.05810 0.05313 -0.0890 0.0006 1.0000
14.250 1.6838 0.06277 0.05792 -0.0896 0.0006 1.0000
14.500 1.6756 0.06736 0.06263 -0.0903 0.0006 1.0000
14.750 1.6677 0.07206 0.06744 -0.0912 0.0006 1.0000
15.000 1.6647 0.07615 0.07164 -0.0921 0.0006 1.0000
15.250 1.6543 0.08161 0.07723 -0.0936 0.0006 1.0000
15.500 1.6471 0.08665 0.08240 -0.0950 0.0005 1.0000
15.750 1.6395 0.09188 0.08776 -0.0965 0.0005 1.0000
16.000 1.6309 0.09745 0.09344 -0.0983 0.0005 1.0000
16.250 1.6220 0.10319 0.09931 -0.1003 0.0005 1.0000
16.500 1.6128 0.10910 0.10534 -0.1025 0.0005 1.0000
16.750 1.6029 0.11529 0.11165 -0.1050 0.0005 1.0000
17.000 1.5938 0.12140 0.11788 -0.1075 0.0005 1.0000
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Polar data table (+)
Polar graphs
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