EPPLER 377 AIRFOIL (e377-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 377 AIRFOIL (e377-il) Reynolds number: 200,000 Max Cl/Cd: 91.3 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e377-il-200000.txt Download as CSV file: xf-e377-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.1947 0.10105 0.09802 -0.0179 1.0000 0.0152
-7.500 -0.1874 0.09891 0.09595 -0.0186 1.0000 0.0155
-7.250 -0.1820 0.09694 0.09407 -0.0188 1.0000 0.0159
-7.000 -0.1618 0.09382 0.09101 -0.0232 0.9748 0.0164
-6.750 -0.1244 0.08952 0.08662 -0.0318 0.9389 0.0171
-6.500 -0.0916 0.08598 0.08296 -0.0388 0.8979 0.0180
-6.250 -0.0710 0.08421 0.08106 -0.0425 0.8635 0.0185
-6.000 -0.0528 0.08317 0.07987 -0.0458 0.8347 0.0188
-5.750 -0.0328 0.08202 0.07861 -0.0498 0.8139 0.0189
-5.500 -0.0108 0.08066 0.07711 -0.0541 0.7946 0.0190
-5.000 0.0146 0.07243 0.06875 -0.0546 0.7684 0.0196
-4.750 0.0283 0.06916 0.06542 -0.0550 0.7561 0.0202
-4.500 0.0475 0.06658 0.06276 -0.0571 0.7448 0.0210
-4.250 0.0695 0.06415 0.06025 -0.0597 0.7342 0.0221
-4.000 0.0940 0.06178 0.05776 -0.0629 0.7252 0.0236
-3.750 0.1443 0.06143 0.05729 -0.0725 0.7146 0.0271
-3.500 0.1902 0.06031 0.05601 -0.0806 0.7056 0.0274
-3.250 0.2025 0.05520 0.05088 -0.0804 0.6984 0.0280
-3.000 0.2175 0.05170 0.04737 -0.0802 0.6907 0.0290
-2.750 0.2440 0.04927 0.04485 -0.0826 0.6836 0.0305
-2.500 0.2759 0.04701 0.04250 -0.0862 0.6758 0.0325
-2.250 0.3128 0.04493 0.04029 -0.0905 0.6692 0.0355
-2.000 0.3797 0.04514 0.04023 -0.1003 0.6614 0.0378
-1.750 0.3949 0.04039 0.03548 -0.1005 0.6556 0.0393
-1.500 0.4202 0.03814 0.03319 -0.1018 0.6491 0.0420
-1.250 0.4554 0.03630 0.03122 -0.1048 0.6426 0.0453
-1.000 0.5119 0.03631 0.03092 -0.1108 0.6365 0.0498
-0.750 0.5470 0.03345 0.02796 -0.1138 0.6302 0.0508
-0.500 0.5695 0.03095 0.02539 -0.1143 0.6251 0.0525
-0.250 0.6001 0.02940 0.02380 -0.1158 0.6186 0.0558
1.000 0.7707 0.02307 0.01669 -0.1234 0.5912 0.0802
1.250 0.8017 0.02211 0.01558 -0.1240 0.5857 0.0851
1.750 0.8774 0.01736 0.00989 -0.1262 0.5761 0.0590
2.000 0.9084 0.01592 0.00797 -0.1263 0.5713 0.0662
2.250 0.9361 0.01589 0.00773 -0.1259 0.5668 0.0896
2.500 0.9620 0.01622 0.00826 -0.1258 0.5606 0.1106
2.750 0.9896 0.01600 0.00788 -0.1255 0.5558 0.1204
3.000 1.0169 0.01587 0.00765 -0.1252 0.5510 0.1269
3.250 1.0439 0.01573 0.00751 -0.1250 0.5452 0.1340
3.500 1.0711 0.01571 0.00742 -0.1247 0.5407 0.1454
3.750 1.0976 0.01578 0.00754 -0.1245 0.5354 0.1598
4.000 1.1241 0.01580 0.00765 -0.1241 0.5297 0.1753
4.250 1.1514 0.01589 0.00767 -0.1239 0.5253 0.1956
4.500 1.1779 0.01599 0.00793 -0.1237 0.5188 0.2194
4.750 1.2043 0.01602 0.00799 -0.1233 0.5132 0.2452
5.000 1.2305 0.01612 0.00814 -0.1229 0.5075 0.2783
5.250 1.2567 0.01613 0.00832 -0.1226 0.5007 0.3246
5.500 1.2858 0.01556 0.00837 -0.1229 0.4950 1.0000
5.750 1.3115 0.01574 0.00860 -0.1225 0.4874 1.0000
6.000 1.3377 0.01591 0.00867 -0.1220 0.4817 1.0000
6.250 1.3628 0.01608 0.00897 -0.1215 0.4735 1.0000
6.500 1.3886 0.01622 0.00912 -0.1210 0.4669 1.0000
6.750 1.4136 0.01636 0.00937 -0.1205 0.4580 1.0000
7.000 1.4388 0.01650 0.00957 -0.1200 0.4497 1.0000
7.250 1.4639 0.01660 0.00970 -0.1194 0.4408 1.0000
7.500 1.4883 0.01673 0.00997 -0.1188 0.4304 1.0000
7.750 1.5127 0.01687 0.01024 -0.1182 0.4197 1.0000
8.000 1.5368 0.01700 0.01046 -0.1175 0.4080 1.0000
8.250 1.5604 0.01716 0.01072 -0.1168 0.3947 1.0000
8.500 1.5836 0.01735 0.01105 -0.1160 0.3790 1.0000
8.750 1.6059 0.01759 0.01137 -0.1152 0.3583 1.0000
9.000 1.6257 0.01798 0.01177 -0.1141 0.3238 1.0000
9.250 1.6422 0.01885 0.01246 -0.1128 0.2747 1.0000
9.500 1.6564 0.02008 0.01351 -0.1114 0.2312 1.0000
9.750 1.6660 0.02180 0.01495 -0.1096 0.1844 1.0000
10.000 1.6730 0.02366 0.01658 -0.1077 0.1447 1.0000
10.250 1.6760 0.02572 0.01839 -0.1054 0.1083 1.0000
10.500 1.6760 0.02783 0.02031 -0.1027 0.0769 1.0000
10.750 1.6659 0.03025 0.02260 -0.0990 0.0511 1.0000
11.000 1.6498 0.03348 0.02570 -0.0958 0.0313 1.0000
11.250 1.6356 0.03721 0.02943 -0.0939 0.0222 1.0000
11.500 1.6238 0.04118 0.03349 -0.0928 0.0189 1.0000
11.750 1.6172 0.04481 0.03730 -0.0922 0.0173 1.0000
12.000 1.6109 0.04854 0.04121 -0.0919 0.0162 1.0000
12.250 1.6039 0.05250 0.04533 -0.0917 0.0152 1.0000
12.500 1.5960 0.05666 0.04964 -0.0917 0.0145 1.0000
12.750 1.5877 0.06098 0.05410 -0.0919 0.0140 1.0000
13.000 1.5785 0.06550 0.05876 -0.0922 0.0136 1.0000
13.250 1.5696 0.07003 0.06342 -0.0925 0.0133 1.0000
13.500 1.5600 0.07474 0.06825 -0.0928 0.0129 1.0000
13.750 1.5522 0.07930 0.07293 -0.0931 0.0126 1.0000
14.000 1.5462 0.08357 0.07732 -0.0930 0.0124 1.0000
14.250 1.5435 0.08730 0.08117 -0.0922 0.0121 1.0000
14.500 1.5437 0.09072 0.08472 -0.0912 0.0120 1.0000
14.750 1.5443 0.09435 0.08853 -0.0908 0.0119 1.0000
15.000 1.5433 0.09843 0.09280 -0.0909 0.0119 1.0000
15.250 1.5399 0.10299 0.09759 -0.0916 0.0118 1.0000
15.500 1.5348 0.10799 0.10280 -0.0931 0.0116 1.0000
15.750 1.5286 0.11329 0.10832 -0.0950 0.0114 1.0000
16.000 1.5212 0.11896 0.11421 -0.0974 0.0113 1.0000
16.250 1.5128 0.12493 0.12044 -0.1001 0.0110 1.0000
16.500 1.5032 0.13135 0.12707 -0.1033 0.0110 1.0000
16.750 1.4929 0.13810 0.13404 -0.1068 0.0109 1.0000
17.000 1.4821 0.14525 0.14139 -0.1110 0.0108 1.0000
17.250 1.4707 0.15279 0.14913 -0.1156 0.0108 1.0000
17.500 1.4586 0.16077 0.15730 -0.1207 0.0108 1.0000
17.750 1.4437 0.16976 0.16648 -0.1265 0.0113 1.0000
18.000 1.4325 0.17840 0.17525 -0.1325 0.0111 1.0000
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Polar data table (+)
Polar graphs
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