EPPLER 396 AIRFOIL (e396-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 396 AIRFOIL (e396-il) Reynolds number: 100,000 Max Cl/Cd: 57.7 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e396-il-100000-n5.txt Download as CSV file: xf-e396-il-100000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.2299 0.09581 0.09102 -0.0790 0.9622 0.0261
-9.750 -0.2253 0.08959 0.08482 -0.0842 0.9574 0.0262
-9.500 -0.2302 0.08265 0.07793 -0.0890 0.9487 0.0264
-9.250 -0.2453 0.07258 0.06790 -0.0966 0.9406 0.0264
-9.000 -0.2760 0.05867 0.05392 -0.1097 0.9300 0.0253
-8.750 -0.3075 0.04534 0.04017 -0.1276 0.9115 0.0243
-8.500 -0.3001 0.03910 0.03335 -0.1357 0.9031 0.0251
-8.250 -0.2893 0.03536 0.02910 -0.1383 0.8942 0.0264
-8.000 -0.2649 0.03222 0.02549 -0.1416 0.8895 0.0289
-7.750 -0.2405 0.03091 0.02407 -0.1431 0.8840 0.0323
-7.500 -0.2166 0.02889 0.02161 -0.1442 0.8780 0.0362
-7.250 -0.1859 0.02744 0.02006 -0.1464 0.8745 0.0413
-7.000 -0.1606 0.02616 0.01841 -0.1469 0.8689 0.0475
-6.750 -0.1341 0.02520 0.01739 -0.1478 0.8636 0.0543
-6.500 -0.1020 0.02403 0.01600 -0.1494 0.8603 0.0623
-6.250 -0.0744 0.02329 0.01504 -0.1499 0.8553 0.0712
-6.000 -0.0483 0.02263 0.01435 -0.1503 0.8498 0.0805
-5.750 -0.0163 0.02187 0.01347 -0.1515 0.8463 0.0912
-5.500 0.0145 0.02126 0.01273 -0.1525 0.8426 0.1040
-5.250 0.0384 0.02087 0.01227 -0.1522 0.8364 0.1161
-5.000 0.0697 0.02040 0.01172 -0.1532 0.8326 0.1318
-4.750 0.1033 0.01993 0.01117 -0.1545 0.8297 0.1495
-4.500 0.1255 0.01977 0.01098 -0.1538 0.8231 0.1657
-4.250 0.1556 0.01948 0.01058 -0.1545 0.8189 0.1849
-4.000 0.1883 0.01915 0.01023 -0.1556 0.8158 0.2051
-3.750 0.2122 0.01907 0.01013 -0.1551 0.8099 0.2241
-3.500 0.2406 0.01892 0.00992 -0.1554 0.8053 0.2452
-3.250 0.2725 0.01869 0.00966 -0.1562 0.8020 0.2671
-3.000 0.2985 0.01865 0.00958 -0.1560 0.7969 0.2882
-2.750 0.3248 0.01859 0.00954 -0.1559 0.7918 0.3092
-2.500 0.3558 0.01844 0.00934 -0.1565 0.7882 0.3329
-2.250 0.3842 0.01836 0.00927 -0.1567 0.7841 0.3554
-2.000 0.4079 0.01843 0.00935 -0.1561 0.7783 0.3779
-1.750 0.4375 0.01833 0.00925 -0.1564 0.7744 0.4022
-1.500 0.4695 0.01818 0.00910 -0.1571 0.7714 0.4288
-1.250 0.4896 0.01838 0.00935 -0.1559 0.7647 0.4524
-1.000 0.5184 0.01832 0.00932 -0.1560 0.7605 0.4799
-0.750 0.5498 0.01820 0.00922 -0.1566 0.7575 0.5100
-0.500 0.5700 0.01840 0.00952 -0.1553 0.7510 0.5373
-0.250 0.5976 0.01839 0.00955 -0.1552 0.7465 0.5695
0.000 0.6283 0.01829 0.00948 -0.1555 0.7433 0.6047
0.250 0.6480 0.01849 0.00981 -0.1541 0.7369 0.6380
0.500 0.6735 0.01850 0.00989 -0.1535 0.7322 0.6762
0.750 0.7018 0.01838 0.00984 -0.1532 0.7289 0.7184
1.000 0.7178 0.01858 0.01018 -0.1509 0.7223 0.7617
1.250 0.7383 0.01853 0.01023 -0.1490 0.7175 0.8149
1.500 0.7617 0.01826 0.01005 -0.1474 0.7141 0.8950
1.750 0.7837 0.01854 0.01035 -0.1468 0.7069 1.0000
2.000 0.8142 0.01866 0.01040 -0.1474 0.7024 1.0000
2.250 0.8486 0.01866 0.01032 -0.1486 0.6991 1.0000
2.500 0.8666 0.01916 0.01084 -0.1473 0.6914 1.0000
2.750 0.8976 0.01923 0.01086 -0.1479 0.6870 1.0000
3.000 0.9235 0.01948 0.01110 -0.1477 0.6816 1.0000
3.250 0.9473 0.01978 0.01142 -0.1472 0.6752 1.0000
3.500 0.9799 0.01979 0.01139 -0.1480 0.6712 1.0000
3.750 0.9987 0.02024 0.01190 -0.1467 0.6636 1.0000
4.000 1.0278 0.02034 0.01201 -0.1470 0.6584 1.0000
4.250 1.0521 0.02059 0.01231 -0.1464 0.6521 1.0000
4.500 1.0763 0.02083 0.01258 -0.1459 0.6453 1.0000
4.750 1.1060 0.02088 0.01265 -0.1461 0.6399 1.0000
5.000 1.1249 0.02127 0.01314 -0.1448 0.6316 1.0000
5.250 1.1551 0.02127 0.01316 -0.1450 0.6257 1.0000
5.500 1.1732 0.02164 0.01362 -0.1435 0.6167 1.0000
5.750 1.1979 0.02178 0.01382 -0.1429 0.6089 1.0000
6.000 1.2220 0.02192 0.01404 -0.1421 0.6004 1.0000
6.250 1.2403 0.02225 0.01446 -0.1406 0.5909 1.0000
6.500 1.2682 0.02224 0.01450 -0.1404 0.5825 1.0000
6.750 1.2861 0.02254 0.01489 -0.1387 0.5718 1.0000
7.000 1.3030 0.02287 0.01534 -0.1369 0.5606 1.0000
7.250 1.3220 0.02310 0.01565 -0.1353 0.5495 1.0000
7.500 1.3416 0.02330 0.01591 -0.1337 0.5378 1.0000
7.750 1.3595 0.02356 0.01623 -0.1320 0.5250 1.0000
8.000 1.3744 0.02393 0.01665 -0.1298 0.5109 1.0000
8.250 1.3867 0.02441 0.01720 -0.1273 0.4956 1.0000
8.500 1.3978 0.02499 0.01787 -0.1247 0.4795 1.0000
8.750 1.4077 0.02565 0.01859 -0.1221 0.4621 1.0000
9.000 1.4174 0.02638 0.01934 -0.1195 0.4434 1.0000
9.250 1.4258 0.02721 0.02017 -0.1168 0.4230 1.0000
9.500 1.4311 0.02827 0.02123 -0.1140 0.4007 1.0000
9.750 1.4355 0.02947 0.02240 -0.1112 0.3771 1.0000
10.000 1.4382 0.03086 0.02372 -0.1084 0.3525 1.0000
10.250 1.4391 0.03249 0.02530 -0.1057 0.3269 1.0000
10.500 1.4388 0.03432 0.02709 -0.1030 0.3015 1.0000
10.750 1.4374 0.03635 0.02903 -0.1006 0.2769 1.0000
11.000 1.4351 0.03857 0.03118 -0.0982 0.2533 1.0000
11.250 1.4331 0.04091 0.03346 -0.0962 0.2305 1.0000
11.750 1.4280 0.04602 0.03847 -0.0926 0.1890 1.0000
12.000 1.4249 0.04881 0.04121 -0.0911 0.1701 1.0000
12.250 1.4221 0.05168 0.04405 -0.0898 0.1525 1.0000
12.500 1.4202 0.05460 0.04696 -0.0887 0.1359 1.0000
12.750 1.4178 0.05767 0.05002 -0.0877 0.1206 1.0000
13.000 1.4155 0.06084 0.05319 -0.0870 0.1071 1.0000
13.250 1.4132 0.06412 0.05650 -0.0863 0.0952 1.0000
13.500 1.4103 0.06757 0.06000 -0.0859 0.0844 1.0000
13.750 1.4064 0.07126 0.06368 -0.0856 0.0755 1.0000
14.000 1.4045 0.07480 0.06731 -0.0854 0.0670 1.0000
14.250 1.4017 0.07853 0.07112 -0.0854 0.0600 1.0000
14.500 1.3971 0.08263 0.07525 -0.0856 0.0541 1.0000
14.750 1.3949 0.08646 0.07919 -0.0858 0.0489 1.0000
15.000 1.3908 0.09067 0.08349 -0.0863 0.0445 1.0000
15.250 1.3862 0.09500 0.08789 -0.0870 0.0409 1.0000
15.500 1.3844 0.09899 0.09204 -0.0876 0.0373 1.0000
15.750 1.3799 0.10347 0.09662 -0.0886 0.0346 1.0000
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