EPPLER 377 (MODIFIED) AIRFOIL (e377m-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 377 (MODIFIED) AIRFOIL (e377m-il) Reynolds number: 1,000,000 Max Cl/Cd: 142.56 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e377m-il-1000000.txt Download as CSV file: xf-e377m-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.1108 0.07719 0.07477 -0.0245 0.6685 0.0055
-7.000 -0.1040 0.07459 0.07214 -0.0250 0.6585 0.0056
-6.750 -0.0949 0.07200 0.06952 -0.0260 0.6485 0.0057
-6.500 -0.0834 0.06929 0.06678 -0.0275 0.6393 0.0058
-6.250 -0.0709 0.06657 0.06404 -0.0292 0.6308 0.0060
-6.000 -0.0577 0.06381 0.06124 -0.0311 0.6227 0.0061
-5.750 -0.0430 0.06098 0.05839 -0.0331 0.6159 0.0062
-5.500 -0.0275 0.05813 0.05551 -0.0353 0.6088 0.0066
-5.250 -0.0104 0.05519 0.05254 -0.0377 0.6025 0.0069
-5.000 0.0070 0.06826 0.06541 -0.0499 0.6137 0.0068
-4.750 0.0297 0.06567 0.06277 -0.0529 0.6066 0.0074
-4.500 0.0557 0.06302 0.06008 -0.0564 0.5997 0.0080
-4.250 0.0840 0.06041 0.05741 -0.0604 0.5931 0.0081
-4.000 0.1135 0.05768 0.05464 -0.0645 0.5870 0.0082
-3.750 0.1445 0.05485 0.05174 -0.0687 0.5810 0.0082
-3.500 0.1703 0.05122 0.04808 -0.0720 0.5760 0.0086
-3.250 0.1973 0.04913 0.04595 -0.0747 0.5703 0.0090
-3.000 0.2266 0.04709 0.04383 -0.0776 0.5647 0.0098
-2.750 0.2591 0.04481 0.04150 -0.0811 0.5596 0.0112
-2.500 0.2972 0.04267 0.03928 -0.0852 0.5545 0.0118
-2.250 0.3327 0.04044 0.03695 -0.0888 0.5496 0.0119
-2.000 0.3681 0.03806 0.03452 -0.0921 0.5451 0.0120
-1.750 0.4061 0.03435 0.03070 -0.0965 0.5405 0.0125
-1.500 0.4326 0.03301 0.02930 -0.0977 0.5356 0.0133
-1.250 0.4647 0.03144 0.02767 -0.0998 0.5315 0.0147
-1.000 0.5026 0.03014 0.02628 -0.1023 0.5268 0.0172
-0.750 0.5368 0.02850 0.02454 -0.1043 0.5222 0.0174
-0.500 0.5707 0.02674 0.02268 -0.1062 0.5181 0.0174
-0.250 0.6050 0.02488 0.02073 -0.1080 0.5140 0.0175
1.000 0.7819 0.01152 0.00612 -0.1158 0.4942 0.0180
1.250 0.8114 0.00970 0.00387 -0.1160 0.4902 0.0195
1.500 0.8391 0.00925 0.00334 -0.1158 0.4859 0.0214
1.750 0.8664 0.00898 0.00298 -0.1156 0.4816 0.0229
2.000 0.8935 0.00881 0.00272 -0.1154 0.4771 0.0248
2.250 0.9198 0.00806 0.00203 -0.1151 0.4733 0.0571
2.500 0.9470 0.00814 0.00214 -0.1149 0.4687 0.0732
2.750 0.9745 0.00841 0.00240 -0.1147 0.4640 0.0784
3.000 1.0019 0.00860 0.00260 -0.1145 0.4595 0.0817
3.250 1.0296 0.00904 0.00310 -0.1143 0.4542 0.0840
3.500 1.0565 0.00935 0.00340 -0.1141 0.4485 0.0848
3.750 1.0837 0.00945 0.00354 -0.1139 0.4431 0.0863
4.000 1.1105 0.00958 0.00365 -0.1137 0.4371 0.0890
4.250 1.1372 0.00929 0.00330 -0.1135 0.4318 0.0946
4.500 1.1642 0.00936 0.00340 -0.1133 0.4261 0.0957
4.750 1.1907 0.00952 0.00354 -0.1131 0.4200 0.0970
5.000 1.2176 0.00960 0.00368 -0.1129 0.4142 0.0989
5.250 1.2440 0.00958 0.00363 -0.1127 0.4074 0.1008
5.500 1.2705 0.00948 0.00353 -0.1125 0.4011 0.1036
5.750 1.2968 0.00948 0.00350 -0.1123 0.3937 0.1062
6.000 1.3232 0.00955 0.00361 -0.1121 0.3863 0.1081
6.500 1.3755 0.00976 0.00387 -0.1117 0.3686 0.1109
6.750 1.4014 0.00987 0.00398 -0.1114 0.3586 0.1124
7.000 1.4270 0.01001 0.00410 -0.1112 0.3481 0.1138
7.250 1.4524 0.01019 0.00426 -0.1109 0.3313 0.1154
7.500 1.4761 0.01066 0.00458 -0.1105 0.2957 0.1168
7.750 1.4973 0.01146 0.00507 -0.1099 0.2408 0.1189
8.000 1.5183 0.01233 0.00571 -0.1092 0.1960 0.1209
8.250 1.5395 0.01312 0.00632 -0.1086 0.1601 0.1232
8.500 1.5594 0.01405 0.00703 -0.1078 0.1218 0.1249
8.750 1.5786 0.01501 0.00779 -0.1070 0.0889 0.1267
9.000 1.5963 0.01610 0.00867 -0.1059 0.0552 0.1280
9.250 1.6074 0.01791 0.01013 -0.1041 0.0125 0.1289
9.500 1.6238 0.01894 0.01115 -0.1028 0.0044 0.1307
9.750 1.6425 0.01966 0.01196 -0.1016 0.0036 0.1327
10.000 1.6597 0.02048 0.01290 -0.1003 0.0032 0.1349
10.250 1.6757 0.02133 0.01385 -0.0989 0.0031 0.1372
10.500 1.6907 0.02217 0.01481 -0.0974 0.0030 0.1397
10.750 1.7031 0.02312 0.01585 -0.0956 0.0028 0.1422
11.000 1.7107 0.02417 0.01702 -0.0930 0.0027 0.1443
11.250 1.7110 0.02537 0.01832 -0.0895 0.0025 0.1456
11.500 1.7104 0.02683 0.01989 -0.0864 0.0024 0.1471
11.750 1.7085 0.02869 0.02185 -0.0840 0.0023 0.1484
12.000 1.7057 0.03093 0.02421 -0.0821 0.0022 0.1501
12.250 1.6997 0.03382 0.02722 -0.0806 0.0021 0.1509
12.500 1.6956 0.03679 0.03031 -0.0798 0.0020 0.1520
12.750 1.6930 0.03979 0.03344 -0.0792 0.0021 0.1538
13.000 1.6839 0.04376 0.03754 -0.0789 0.0020 0.1551
13.250 1.6755 0.04780 0.04171 -0.0789 0.0019 0.1565
13.500 1.6673 0.05198 0.04603 -0.0790 0.0019 0.1578
13.750 1.6608 0.05601 0.05018 -0.0794 0.0019 0.1597
14.000 1.6509 0.06063 0.05492 -0.0799 0.0019 0.1609
14.250 1.6412 0.06537 0.05979 -0.0806 0.0019 0.1622
14.500 1.6321 0.07021 0.06475 -0.0815 0.0019 0.1633
14.750 1.6253 0.07487 0.06953 -0.0825 0.0019 0.1653
15.000 1.6187 0.07966 0.07444 -0.0836 0.0019 0.1678
15.250 1.6125 0.08449 0.07939 -0.0849 0.0019 0.1704
15.500 1.6051 0.08964 0.08467 -0.0863 0.0019 0.1728
15.750 1.5989 0.09471 0.08987 -0.0878 0.0020 0.1753
16.000 1.5925 0.09990 0.09519 -0.0894 0.0020 0.1777
16.250 1.5860 0.10521 0.10065 -0.0911 0.0020 0.1813
16.500 1.5784 0.11081 0.10641 -0.0930 0.0021 0.1846
16.750 1.5694 0.11673 0.11251 -0.0950 0.0022 0.1876
17.000 1.5578 0.12335 0.11934 -0.0974 0.0024 0.1902
17.250 1.5460 0.13019 0.12637 -0.1003 0.0025 0.1928
17.500 1.5341 0.13727 0.13363 -0.1037 0.0026 0.1964
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Polar data table (+)
Polar graphs
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