EPPLER 377 AIRFOIL (e377-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: EPPLER 377 AIRFOIL (e377-il) Reynolds number: 100,000 Max Cl/Cd: 66.82 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e377-il-100000-n5.txt Download as CSV file: xf-e377-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.2079 0.10623 0.10183 -0.0162 1.0000 0.0205
-7.750 -0.1997 0.10427 0.09995 -0.0172 1.0000 0.0210
-7.500 -0.1928 0.10275 0.09852 -0.0183 1.0000 0.0214
-7.250 -0.1792 0.10091 0.09676 -0.0213 0.9698 0.0216
-7.000 -0.1482 0.09830 0.09410 -0.0294 0.9235 0.0218
-6.750 -0.1210 0.09606 0.09177 -0.0361 0.8884 0.0220
-6.500 -0.0989 0.09398 0.08959 -0.0408 0.8559 0.0220
-6.250 -0.0796 0.09200 0.08750 -0.0444 0.8296 0.0221
-6.000 -0.0765 0.08475 0.08023 -0.0402 0.8152 0.0229
-5.750 -0.0638 0.08171 0.07710 -0.0407 0.7963 0.0240
-5.500 -0.0477 0.07925 0.07457 -0.0426 0.7829 0.0258
-5.250 -0.0295 0.07691 0.07216 -0.0451 0.7684 0.0275
-5.000 -0.0075 0.07476 0.06992 -0.0486 0.7561 0.0294
-4.750 0.0241 0.07375 0.06879 -0.0549 0.7426 0.0306
-4.500 0.0601 0.07277 0.06770 -0.0624 0.7316 0.0309
-4.250 0.0950 0.07110 0.06592 -0.0688 0.7215 0.0311
-4.000 0.0942 0.06500 0.05983 -0.0644 0.7134 0.0319
-3.750 0.1120 0.06177 0.05657 -0.0653 0.7042 0.0331
-3.500 0.1368 0.05920 0.05390 -0.0680 0.6962 0.0348
-3.250 0.1661 0.05677 0.05140 -0.0718 0.6878 0.0369
-3.000 0.2311 0.05720 0.05152 -0.0838 0.6793 0.0416
-2.750 0.2627 0.05393 0.04817 -0.0877 0.6721 0.0422
-2.500 0.2752 0.04975 0.04400 -0.0868 0.6654 0.0433
-2.250 0.3011 0.04709 0.04126 -0.0887 0.6582 0.0452
-2.000 0.3338 0.04487 0.03892 -0.0919 0.6515 0.0475
-1.750 0.3702 0.04282 0.03673 -0.0957 0.6445 0.0504
-1.500 0.4215 0.04185 0.03549 -0.1021 0.6382 0.0542
-1.000 0.4841 0.03694 0.03034 -0.1068 0.6262 0.0575
-0.750 0.5156 0.03522 0.02855 -0.1088 0.6192 0.0623
-0.500 0.5529 0.03362 0.02674 -0.1115 0.6137 0.0645
0.000 0.6346 0.02925 0.02182 -0.1176 0.6020 0.0399
0.250 0.6684 0.02768 0.02003 -0.1191 0.5971 0.0384
0.500 0.7035 0.02615 0.01830 -0.1208 0.5909 0.0375
0.750 0.7385 0.02462 0.01648 -0.1221 0.5859 0.0373
1.000 0.7744 0.02292 0.01444 -0.1234 0.5807 0.0402
1.250 0.8054 0.02196 0.01328 -0.1240 0.5750 0.0452
1.500 0.8377 0.02059 0.01149 -0.1244 0.5705 0.0483
1.750 0.8700 0.01908 0.00944 -0.1249 0.5651 0.0557
2.000 0.8971 0.01906 0.00938 -0.1246 0.5596 0.0723
2.250 0.9246 0.01912 0.00921 -0.1244 0.5552 0.0947
2.500 0.9526 0.01912 0.00915 -0.1244 0.5490 0.1078
2.750 0.9809 0.01901 0.00897 -0.1243 0.5440 0.1142
3.000 1.0087 0.01890 0.00870 -0.1241 0.5392 0.1224
3.250 1.0353 0.01898 0.00878 -0.1239 0.5333 0.1352
3.500 1.0617 0.01901 0.00875 -0.1234 0.5287 0.1480
3.750 1.0879 0.01911 0.00886 -0.1231 0.5234 0.1610
4.000 1.1138 0.01926 0.00913 -0.1228 0.5178 0.1798
4.250 1.1399 0.01938 0.00920 -0.1223 0.5134 0.2004
4.500 1.1655 0.01961 0.00957 -0.1220 0.5072 0.2248
4.750 1.1912 0.01978 0.00979 -0.1216 0.5018 0.2522
5.000 1.2170 0.01995 0.01010 -0.1212 0.4965 0.2899
5.250 1.2423 0.02007 0.01049 -0.1209 0.4898 0.3753
5.500 1.2699 0.01975 0.01058 -0.1207 0.4845 1.0000
5.750 1.2946 0.02012 0.01105 -0.1203 0.4766 1.0000
6.000 1.3200 0.02031 0.01120 -0.1197 0.4705 1.0000
6.250 1.3442 0.02067 0.01177 -0.1192 0.4618 1.0000
6.500 1.3691 0.02089 0.01202 -0.1185 0.4546 1.0000
6.750 1.3932 0.02119 0.01244 -0.1179 0.4456 1.0000
7.000 1.4172 0.02148 0.01286 -0.1173 0.4366 1.0000
7.250 1.4414 0.02168 0.01311 -0.1165 0.4276 1.0000
7.500 1.4646 0.02199 0.01358 -0.1158 0.4164 1.0000
7.750 1.4875 0.02230 0.01413 -0.1150 0.4043 1.0000
8.000 1.5101 0.02260 0.01460 -0.1142 0.3910 1.0000
8.250 1.5321 0.02294 0.01508 -0.1133 0.3762 1.0000
8.500 1.5534 0.02331 0.01558 -0.1123 0.3596 1.0000
8.750 1.5735 0.02381 0.01623 -0.1112 0.3396 1.0000
9.000 1.5923 0.02440 0.01690 -0.1100 0.3168 1.0000
9.250 1.6090 0.02520 0.01783 -0.1087 0.2888 1.0000
9.500 1.6226 0.02629 0.01891 -0.1071 0.2554 1.0000
9.750 1.6297 0.02794 0.02035 -0.1051 0.2151 1.0000
10.000 1.6315 0.03001 0.02221 -0.1028 0.1792 1.0000
10.250 1.6299 0.03227 0.02431 -0.1003 0.1477 1.0000
10.500 1.6238 0.03458 0.02653 -0.0974 0.1260 1.0000
10.750 1.6175 0.03699 0.02895 -0.0950 0.1104 1.0000
11.000 1.6111 0.03978 0.03177 -0.0934 0.0972 1.0000
11.250 1.6029 0.04309 0.03509 -0.0924 0.0826 1.0000
11.500 1.5933 0.04686 0.03883 -0.0918 0.0676 1.0000
11.750 1.5836 0.05089 0.04284 -0.0916 0.0543 1.0000
12.000 1.5741 0.05508 0.04705 -0.0915 0.0429 1.0000
12.250 1.5640 0.05951 0.05152 -0.0917 0.0334 1.0000
12.500 1.5531 0.06418 0.05623 -0.0920 0.0262 1.0000
12.750 1.5408 0.06919 0.06125 -0.0925 0.0212 1.0000
13.000 1.5311 0.07398 0.06618 -0.0931 0.0179 1.0000
13.250 1.5211 0.07893 0.07126 -0.0939 0.0157 1.0000
13.500 1.5098 0.08422 0.07673 -0.0949 0.0143 1.0000
13.750 1.4990 0.08973 0.08237 -0.0963 0.0132 1.0000
14.000 1.4908 0.09495 0.08779 -0.0976 0.0124 1.0000
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Polar data table (+)
Polar graphs
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