EPPLER 377 AIRFOIL (e377-il) Xfoil prediction polar at RE=500,000 Ncrit=5
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Airfoil: EPPLER 377 AIRFOIL (e377-il) Reynolds number: 500,000 Max Cl/Cd: 130.13 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e377-il-500000-n5.txt Download as CSV file: xf-e377-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.1687 0.09776 0.09453 -0.0250 0.6865 0.0057
-7.500 -0.1605 0.09549 0.09225 -0.0260 0.6767 0.0058
-7.250 -0.1530 0.09236 0.08908 -0.0263 0.6668 0.0059
-7.000 -0.1438 0.09013 0.08683 -0.0269 0.6572 0.0063
-6.750 -0.1322 0.08786 0.08453 -0.0284 0.6476 0.0064
-6.500 -0.1191 0.08569 0.08233 -0.0300 0.6404 0.0073
-6.250 -0.1038 0.08337 0.07998 -0.0321 0.6316 0.0085
-6.000 -0.0876 0.08100 0.07758 -0.0346 0.6245 0.0087
-5.750 -0.0703 0.07854 0.07510 -0.0372 0.6178 0.0088
-5.500 -0.0516 0.07602 0.07254 -0.0401 0.6109 0.0089
-5.250 -0.0318 0.07343 0.06992 -0.0432 0.6041 0.0089
-5.000 -0.0105 0.07079 0.06722 -0.0465 0.5977 0.0089
-4.750 0.0122 0.06806 0.06447 -0.0499 0.5917 0.0090
-4.500 0.0362 0.06530 0.06166 -0.0534 0.5860 0.0090
-4.250 0.0615 0.06247 0.05879 -0.0571 0.5806 0.0090
-4.000 0.0890 0.05951 0.05578 -0.0612 0.5747 0.0090
-3.750 0.1179 0.05653 0.05273 -0.0653 0.5696 0.0090
-3.500 0.1499 0.05351 0.04967 -0.0699 0.5647 0.0091
-3.250 0.1761 0.05014 0.04626 -0.0733 0.5597 0.0096
-3.000 0.2009 0.04861 0.04468 -0.0752 0.5547 0.0117
-2.750 0.2451 0.04652 0.04249 -0.0813 0.5494 0.0140
-2.500 0.2816 0.04390 0.03977 -0.0858 0.5444 0.0141
-2.250 0.3180 0.04123 0.03702 -0.0900 0.5402 0.0141
-2.000 0.3557 0.03852 0.03422 -0.0942 0.5356 0.0142
-1.500 0.4226 0.03337 0.02889 -0.1007 0.5265 0.0160
-1.250 0.4580 0.03146 0.02689 -0.1036 0.5221 0.0167
-0.750 0.5398 0.02656 0.02167 -0.1107 0.5135 0.0138
-0.500 0.5778 0.02430 0.01927 -0.1135 0.5094 0.0138
0.000 0.6544 0.01957 0.01415 -0.1184 0.5011 0.0153
0.250 0.6842 0.01885 0.01334 -0.1191 0.4970 0.0170
0.500 0.7343 0.01149 0.00484 -0.1230 0.4938 0.0154
0.750 0.7628 0.01084 0.00393 -0.1230 0.4894 0.0154
1.000 0.7907 0.01042 0.00333 -0.1228 0.4854 0.0156
1.250 0.8185 0.01011 0.00292 -0.1226 0.4813 0.0160
1.500 0.8461 0.00991 0.00264 -0.1224 0.4766 0.0170
1.750 0.8734 0.00979 0.00245 -0.1221 0.4724 0.0189
2.000 0.9008 0.00973 0.00233 -0.1219 0.4685 0.0215
2.250 0.9280 0.00964 0.00230 -0.1216 0.4639 0.0384
2.500 0.9551 0.00967 0.00234 -0.1214 0.4594 0.0536
2.750 0.9821 0.00972 0.00238 -0.1211 0.4553 0.0607
3.000 1.0092 0.00976 0.00243 -0.1209 0.4507 0.0679
3.250 1.0362 0.00981 0.00251 -0.1206 0.4458 0.0797
3.500 1.0631 0.00988 0.00258 -0.1204 0.4413 0.0873
3.750 1.0901 0.00993 0.00266 -0.1202 0.4357 0.0962
4.000 1.1168 0.01002 0.00277 -0.1199 0.4297 0.1065
4.250 1.1436 0.01009 0.00288 -0.1197 0.4234 0.1175
4.500 1.1702 0.01020 0.00300 -0.1194 0.4164 0.1302
4.750 1.1968 0.01030 0.00314 -0.1192 0.4098 0.1455
5.000 1.2232 0.01042 0.00332 -0.1189 0.4026 0.1617
5.250 1.2497 0.01053 0.00348 -0.1187 0.3956 0.1797
5.500 1.2759 0.01068 0.00366 -0.1184 0.3874 0.1996
5.750 1.3022 0.01081 0.00386 -0.1182 0.3786 0.2239
6.000 1.3282 0.01098 0.00407 -0.1179 0.3692 0.2511
6.250 1.3539 0.01116 0.00433 -0.1176 0.3582 0.2942
6.500 1.3820 0.01062 0.00459 -0.1180 0.3456 1.0000
6.750 1.4073 0.01090 0.00484 -0.1177 0.3317 1.0000
7.000 1.4322 0.01123 0.00513 -0.1173 0.3150 1.0000
7.250 1.4560 0.01172 0.00551 -0.1168 0.2872 1.0000
7.500 1.4767 0.01269 0.00620 -0.1162 0.2329 1.0000
7.750 1.4971 0.01368 0.00693 -0.1155 0.1887 1.0000
8.000 1.5172 0.01467 0.00771 -0.1148 0.1509 1.0000
8.250 1.5348 0.01593 0.00867 -0.1138 0.1045 1.0000
8.500 1.5505 0.01737 0.00979 -0.1127 0.0611 1.0000
8.750 1.5680 0.01847 0.01075 -0.1116 0.0375 1.0000
9.000 1.5835 0.01972 0.01186 -0.1103 0.0164 1.0000
9.250 1.5970 0.02111 0.01322 -0.1087 0.0042 1.0000
9.500 1.6141 0.02199 0.01420 -0.1075 0.0033 1.0000
9.750 1.6304 0.02287 0.01519 -0.1061 0.0030 1.0000
10.000 1.6453 0.02380 0.01623 -0.1047 0.0029 1.0000
10.250 1.6579 0.02483 0.01738 -0.1030 0.0027 1.0000
10.500 1.6672 0.02594 0.01861 -0.1008 0.0025 1.0000
10.750 1.6705 0.02720 0.01998 -0.0980 0.0023 1.0000
11.000 1.6719 0.02873 0.02163 -0.0956 0.0022 1.0000
11.250 1.6723 0.03063 0.02365 -0.0936 0.0020 1.0000
11.500 1.6716 0.03291 0.02609 -0.0922 0.0019 1.0000
11.750 1.6696 0.03561 0.02893 -0.0912 0.0018 1.0000
12.000 1.6656 0.03876 0.03223 -0.0906 0.0018 1.0000
12.250 1.6597 0.04234 0.03595 -0.0902 0.0017 1.0000
12.500 1.6557 0.04580 0.03954 -0.0900 0.0017 1.0000
12.750 1.6442 0.05035 0.04425 -0.0901 0.0016 1.0000
13.000 1.6384 0.05425 0.04828 -0.0902 0.0016 1.0000
13.250 1.6342 0.05801 0.05216 -0.0905 0.0016 1.0000
13.500 1.6282 0.06209 0.05637 -0.0908 0.0015 1.0000
13.750 1.6225 0.06622 0.06063 -0.0913 0.0015 1.0000
14.000 1.6151 0.07071 0.06524 -0.0920 0.0015 1.0000
14.250 1.6091 0.07520 0.06986 -0.0929 0.0015 1.0000
14.500 1.6018 0.08003 0.07482 -0.0939 0.0014 1.0000
14.750 1.5945 0.08497 0.07989 -0.0951 0.0014 1.0000
15.000 1.5881 0.08992 0.08497 -0.0964 0.0014 1.0000
15.250 1.5802 0.09526 0.09045 -0.0980 0.0013 1.0000
15.500 1.5730 0.10055 0.09587 -0.0996 0.0013 1.0000
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Polar data table (+)
Polar graphs
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