EPPLER 396 AIRFOIL (e396-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 396 AIRFOIL (e396-il) Reynolds number: 100,000 Max Cl/Cd: 54.68 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e396-il-100000.txt Download as CSV file: xf-e396-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 396 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.2821 0.11359 0.10938 -0.0504 0.9778 0.1070
-8.500 -0.2904 0.11074 0.10657 -0.0588 0.9714 0.1122
-8.250 -0.3111 0.10876 0.10468 -0.0642 0.9617 0.1129
-8.000 -0.2566 0.10290 0.09871 -0.0597 0.9621 0.1205
-7.750 -0.2683 0.10034 0.09620 -0.0649 0.9543 0.1259
-7.500 -0.2870 0.09781 0.09375 -0.0701 0.9454 0.1268
-7.250 -0.3178 0.08161 0.07758 -0.0770 0.9369 0.0732
-7.000 -0.3091 0.07426 0.07019 -0.0847 0.9314 0.0698
-6.750 -0.3038 0.07458 0.07054 -0.0818 0.9244 0.0767
-6.500 -0.3108 0.04406 0.03821 -0.1170 0.9176 0.0602
-6.250 -0.2921 0.04376 0.03812 -0.1163 0.9120 0.0659
-6.000 -0.2576 0.03845 0.03161 -0.1219 0.9078 0.0725
-5.750 -0.2220 0.03667 0.02969 -0.1246 0.9043 0.0825
-5.500 -0.1790 0.03480 0.02748 -0.1285 0.9018 0.0955
-5.250 -0.1638 0.03387 0.02637 -0.1274 0.8950 0.1040
-5.000 -0.1282 0.03266 0.02491 -0.1295 0.8910 0.1174
-4.750 -0.0872 0.03179 0.02387 -0.1323 0.8881 0.1348
-4.500 -0.0690 0.03142 0.02340 -0.1314 0.8817 0.1471
-4.250 -0.0366 0.03094 0.02281 -0.1326 0.8772 0.1662
-4.000 0.0034 0.03039 0.02221 -0.1351 0.8741 0.1893
-3.750 0.0215 0.03043 0.02225 -0.1341 0.8676 0.2069
-3.500 0.0525 0.03026 0.02200 -0.1350 0.8628 0.2315
-3.250 0.0924 0.02997 0.02168 -0.1373 0.8596 0.2602
-3.000 0.1077 0.03026 0.02205 -0.1358 0.8527 0.2796
-2.750 0.1390 0.03022 0.02200 -0.1367 0.8479 0.3073
-2.500 0.1790 0.03003 0.02182 -0.1389 0.8449 0.3391
-2.250 0.1906 0.03054 0.02235 -0.1369 0.8372 0.3603
-2.000 0.2238 0.03052 0.02236 -0.1379 0.8328 0.3910
-1.750 0.2650 0.03033 0.02220 -0.1401 0.8300 0.4260
-1.500 0.2711 0.03104 0.02299 -0.1373 0.8213 0.4462
-1.250 0.3070 0.03097 0.02296 -0.1386 0.8174 0.4819
-1.000 0.3290 0.03135 0.02341 -0.1380 0.8116 0.5124
-0.750 0.3507 0.03167 0.02381 -0.1373 0.8052 0.5447
-0.500 0.3884 0.03149 0.02374 -0.1385 0.8019 0.5872
-0.250 0.3962 0.03232 0.02467 -0.1359 0.7936 0.6187
0.000 0.4267 0.03229 0.02478 -0.1360 0.7891 0.6652
0.250 0.4644 0.03195 0.02457 -0.1367 0.7865 0.7237
0.500 0.4607 0.03299 0.02578 -0.1322 0.7764 0.7688
0.750 0.4831 0.03248 0.02550 -0.1297 0.7730 0.8634
1.000 0.4933 0.03339 0.02640 -0.1285 0.7634 1.0000
1.250 0.5359 0.03351 0.02631 -0.1313 0.7595 1.0000
1.500 0.5776 0.03358 0.02622 -0.1336 0.7562 1.0000
1.750 0.5850 0.03491 0.02748 -0.1318 0.7462 1.0000
2.000 0.6290 0.03476 0.02722 -0.1341 0.7435 1.0000
2.250 0.6320 0.03634 0.02876 -0.1317 0.7329 1.0000
2.500 0.6737 0.03620 0.02855 -0.1335 0.7297 1.0000
2.750 0.6790 0.03774 0.03006 -0.1314 0.7194 1.0000
3.000 0.7187 0.03761 0.02988 -0.1329 0.7158 1.0000
3.250 0.7265 0.03907 0.03132 -0.1311 0.7059 1.0000
3.500 0.7642 0.03897 0.03121 -0.1323 0.7018 1.0000
3.750 0.8008 0.03891 0.03114 -0.1332 0.6977 1.0000
4.250 0.8409 0.04046 0.03272 -0.1319 0.6824 1.0000
4.500 0.8573 0.04140 0.03368 -0.1308 0.6734 1.0000
4.750 0.8715 0.04256 0.03486 -0.1296 0.6644 1.0000
5.000 0.9059 0.04235 0.03469 -0.1300 0.6591 1.0000
5.250 0.9546 0.04115 0.03356 -0.1317 0.6570 1.0000
5.500 1.0067 0.03957 0.03205 -0.1335 0.6555 1.0000
5.750 0.9725 0.04393 0.03643 -0.1281 0.6355 1.0000
6.000 1.0116 0.04310 0.03570 -0.1286 0.6307 1.0000
6.250 1.0640 0.04114 0.03384 -0.1300 0.6289 1.0000
6.500 1.1070 0.03983 0.03262 -0.1307 0.6249 1.0000
6.750 1.1908 0.03593 0.02891 -0.1357 0.6265 1.0000
7.000 1.1959 0.03690 0.02995 -0.1326 0.6146 1.0000
7.250 1.2788 0.03335 0.02660 -0.1382 0.6130 1.0000
7.500 1.2832 0.03407 0.02742 -0.1345 0.6009 1.0000
7.750 1.3034 0.03395 0.02741 -0.1328 0.5902 1.0000
8.000 1.3947 0.02998 0.02358 -0.1396 0.5845 1.0000
8.250 1.4177 0.02955 0.02330 -0.1381 0.5714 1.0000
8.500 1.4451 0.02890 0.02276 -0.1370 0.5578 1.0000
8.750 1.4750 0.02810 0.02204 -0.1363 0.5426 1.0000
9.000 1.5015 0.02746 0.02145 -0.1351 0.5252 1.0000
9.250 1.5060 0.02771 0.02179 -0.1309 0.5071 1.0000
9.500 1.5165 0.02777 0.02189 -0.1275 0.4869 1.0000
9.750 1.5252 0.02800 0.02217 -0.1241 0.4651 1.0000
10.000 1.5276 0.02862 0.02279 -0.1201 0.4419 1.0000
10.250 1.5265 0.02957 0.02374 -0.1159 0.4170 1.0000
10.500 1.5250 0.03072 0.02483 -0.1120 0.3905 1.0000
10.750 1.5210 0.03220 0.02622 -0.1081 0.3629 1.0000
11.000 1.5148 0.03402 0.02794 -0.1044 0.3346 1.0000
11.250 1.5072 0.03617 0.02995 -0.1010 0.3063 1.0000
11.500 1.4986 0.03862 0.03225 -0.0978 0.2786 1.0000
11.750 1.4894 0.04132 0.03479 -0.0949 0.2523 1.0000
12.000 1.4800 0.04426 0.03762 -0.0924 0.2266 1.0000
12.250 1.4706 0.04740 0.04065 -0.0902 0.2026 1.0000
12.500 1.4612 0.05072 0.04377 -0.0882 0.1811 1.0000
12.750 1.4529 0.05415 0.04715 -0.0866 0.1598 1.0000
13.000 1.4450 0.05769 0.05051 -0.0851 0.1417 1.0000
13.250 1.4390 0.06122 0.05401 -0.0839 0.1246 1.0000
13.500 1.4346 0.06473 0.05746 -0.0829 0.1095 1.0000
13.750 1.4314 0.06819 0.06088 -0.0820 0.0967 1.0000
14.000 1.4307 0.07147 0.06410 -0.0811 0.0856 1.0000
14.250 1.4327 0.07448 0.06698 -0.0803 0.0757 1.0000
14.500 1.4328 0.07788 0.07057 -0.0798 0.0681 1.0000
14.750 1.4384 0.08074 0.07346 -0.0790 0.0609 1.0000
15.000 1.4406 0.08387 0.07660 -0.0787 0.0553 1.0000
15.250 1.4501 0.08667 0.07954 -0.0777 0.0500 1.0000
15.500 1.4503 0.09018 0.08323 -0.0776 0.0463 1.0000
15.750 1.4629 0.09283 0.08581 -0.0768 0.0419 1.0000
16.000 1.4595 0.09714 0.09049 -0.0770 0.0403 1.0000
16.250 1.4550 0.10160 0.09525 -0.0775 0.0385 1.0000
16.500 1.4502 0.10603 0.09991 -0.0782 0.0370 1.0000
16.750 1.4454 0.11030 0.10437 -0.0793 0.0353 1.0000
17.000 1.4503 0.11397 0.10802 -0.0796 0.0332 1.0000
17.250 1.4364 0.12017 0.11449 -0.0816 0.0327 1.0000
17.500 1.4210 0.12638 0.12100 -0.0843 0.0326 1.0000
17.750 1.4038 0.13318 0.12808 -0.0877 0.0325 1.0000
18.000 1.3866 0.14035 0.13552 -0.0915 0.0325 1.0000
18.250 1.3685 0.14800 0.14341 -0.0961 0.0326 1.0000
18.500 1.3492 0.15635 0.15197 -0.1014 0.0327 1.0000
18.750 1.3312 0.16488 0.16071 -0.1071 0.0329 1.0000
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Polar data table (+)
Polar graphs
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