EPPLER 398 AIRFOIL (e398-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 398 AIRFOIL (e398-il) Reynolds number: 100,000 Max Cl/Cd: 54.92 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e398-il-100000-n5.txt Download as CSV file: xf-e398-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 398 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 -0.3969 0.05391 0.04880 -0.1070 0.9453 0.0243
-9.750 -0.4078 0.04577 0.04028 -0.1186 0.9302 0.0244
-9.500 -0.3969 0.04198 0.03633 -0.1246 0.9184 0.0253
-9.250 -0.3808 0.03902 0.03313 -0.1288 0.9092 0.0267
-9.000 -0.3638 0.03551 0.02916 -0.1326 0.9008 0.0286
-8.750 -0.3454 0.03304 0.02639 -0.1343 0.8920 0.0303
-8.500 -0.3192 0.03126 0.02439 -0.1367 0.8854 0.0338
-8.250 -0.2959 0.02956 0.02248 -0.1380 0.8778 0.0373
-8.000 -0.2696 0.02797 0.02055 -0.1394 0.8708 0.0422
-7.750 -0.2408 0.02675 0.01926 -0.1411 0.8651 0.0476
-7.500 -0.2168 0.02566 0.01802 -0.1415 0.8570 0.0536
-7.250 -0.1853 0.02453 0.01666 -0.1432 0.8520 0.0617
-7.000 -0.1611 0.02378 0.01577 -0.1433 0.8439 0.0695
-6.750 -0.1315 0.02294 0.01484 -0.1444 0.8382 0.0783
-6.500 -0.1032 0.02219 0.01396 -0.1451 0.8321 0.0879
-6.250 -0.0765 0.02156 0.01321 -0.1454 0.8250 0.0985
-6.000 -0.0448 0.02090 0.01242 -0.1465 0.8202 0.1110
-5.750 -0.0195 0.02048 0.01189 -0.1465 0.8130 0.1236
-5.500 0.0097 0.02001 0.01133 -0.1471 0.8072 0.1384
-5.250 0.0403 0.01956 0.01083 -0.1480 0.8023 0.1548
-5.000 0.0655 0.01928 0.01051 -0.1478 0.7951 0.1706
-4.750 0.0956 0.01894 0.01012 -0.1485 0.7901 0.1887
-4.500 0.1240 0.01870 0.00983 -0.1488 0.7847 0.2076
-4.250 0.1506 0.01853 0.00961 -0.1488 0.7783 0.2264
-4.000 0.1810 0.01832 0.00929 -0.1494 0.7736 0.2474
-3.750 0.2084 0.01819 0.00915 -0.1495 0.7682 0.2666
-3.500 0.2351 0.01810 0.00904 -0.1494 0.7623 0.2858
-3.250 0.2651 0.01797 0.00883 -0.1499 0.7579 0.3067
-3.000 0.2926 0.01791 0.00872 -0.1499 0.7527 0.3268
-2.750 0.3189 0.01789 0.00869 -0.1498 0.7469 0.3463
-2.500 0.3481 0.01780 0.00857 -0.1500 0.7426 0.3663
-2.250 0.3767 0.01776 0.00850 -0.1502 0.7382 0.3866
-2.000 0.4017 0.01780 0.00856 -0.1498 0.7323 0.4064
-1.750 0.4300 0.01778 0.00849 -0.1499 0.7278 0.4274
-1.500 0.4601 0.01771 0.00841 -0.1502 0.7243 0.4486
-1.250 0.4833 0.01783 0.00858 -0.1496 0.7183 0.4686
-1.000 0.5103 0.01786 0.00862 -0.1494 0.7135 0.4908
-0.750 0.5396 0.01784 0.00859 -0.1496 0.7098 0.5139
-0.500 0.5648 0.01794 0.00873 -0.1492 0.7050 0.5369
-0.250 0.5897 0.01805 0.00889 -0.1487 0.6998 0.5613
0.000 0.6172 0.01807 0.00894 -0.1486 0.6957 0.5869
0.250 0.6466 0.01806 0.00894 -0.1487 0.6924 0.6143
0.500 0.6678 0.01829 0.00927 -0.1476 0.6865 0.6413
0.750 0.6928 0.01836 0.00942 -0.1470 0.6819 0.6702
1.000 0.7201 0.01837 0.00946 -0.1466 0.6783 0.7017
1.250 0.7423 0.01851 0.00969 -0.1455 0.6737 0.7345
1.500 0.7624 0.01866 0.00995 -0.1440 0.6684 0.7702
1.750 0.7844 0.01865 0.01003 -0.1425 0.6644 0.8114
2.000 0.8074 0.01854 0.00997 -0.1410 0.6612 0.8643
2.250 0.8272 0.01869 0.01025 -0.1397 0.6551 1.0000
2.500 0.8556 0.01893 0.01044 -0.1401 0.6505 1.0000
2.750 0.8871 0.01908 0.01051 -0.1410 0.6469 1.0000
3.000 0.9123 0.01943 0.01086 -0.1408 0.6419 1.0000
3.250 0.9366 0.01978 0.01121 -0.1405 0.6364 1.0000
3.500 0.9659 0.01997 0.01136 -0.1410 0.6324 1.0000
3.750 0.9951 0.02017 0.01155 -0.1413 0.6283 1.0000
4.000 1.0148 0.02067 0.01211 -0.1403 0.6220 1.0000
4.250 1.0427 0.02087 0.01232 -0.1404 0.6174 1.0000
4.500 1.0751 0.02095 0.01237 -0.1412 0.6139 1.0000
4.750 1.0905 0.02157 0.01311 -0.1395 0.6066 1.0000
5.000 1.1177 0.02178 0.01334 -0.1395 0.6017 1.0000
5.250 1.1473 0.02191 0.01349 -0.1398 0.5972 1.0000
5.500 1.1633 0.02248 0.01418 -0.1382 0.5898 1.0000
5.750 1.1923 0.02258 0.01430 -0.1383 0.5847 1.0000
6.000 1.2124 0.02300 0.01482 -0.1372 0.5780 1.0000
6.250 1.2347 0.02328 0.01518 -0.1364 0.5713 1.0000
6.500 1.2627 0.02337 0.01531 -0.1363 0.5654 1.0000
6.750 1.2774 0.02388 0.01596 -0.1344 0.5569 1.0000
7.000 1.3069 0.02386 0.01596 -0.1345 0.5506 1.0000
7.250 1.3181 0.02444 0.01669 -0.1320 0.5413 1.0000
7.500 1.3424 0.02455 0.01688 -0.1313 0.5337 1.0000
7.750 1.3565 0.02497 0.01742 -0.1292 0.5242 1.0000
8.000 1.3698 0.02537 0.01792 -0.1268 0.5146 1.0000
8.250 1.3932 0.02537 0.01795 -0.1259 0.5051 1.0000
8.500 1.3962 0.02610 0.01882 -0.1222 0.4936 1.0000
8.750 1.4055 0.02668 0.01951 -0.1194 0.4821 1.0000
9.000 1.4173 0.02717 0.02007 -0.1171 0.4701 1.0000
9.250 1.4285 0.02772 0.02068 -0.1148 0.4571 1.0000
9.500 1.4366 0.02845 0.02148 -0.1122 0.4429 1.0000
9.750 1.4422 0.02939 0.02248 -0.1095 0.4277 1.0000
10.000 1.4460 0.03053 0.02369 -0.1068 0.4112 1.0000
10.250 1.4490 0.03183 0.02502 -0.1042 0.3935 1.0000
10.500 1.4517 0.03324 0.02645 -0.1017 0.3744 1.0000
10.750 1.4540 0.03477 0.02794 -0.0994 0.3542 1.0000
11.000 1.4538 0.03662 0.02977 -0.0971 0.3329 1.0000
11.250 1.4524 0.03868 0.03179 -0.0949 0.3113 1.0000
11.500 1.4496 0.04096 0.03402 -0.0929 0.2898 1.0000
11.750 1.4460 0.04347 0.03648 -0.0910 0.2684 1.0000
12.000 1.4413 0.04620 0.03913 -0.0894 0.2480 1.0000
12.250 1.4369 0.04905 0.04195 -0.0879 0.2286 1.0000
12.500 1.4323 0.05207 0.04493 -0.0867 0.2098 1.0000
12.750 1.4276 0.05522 0.04805 -0.0857 0.1922 1.0000
13.000 1.4229 0.05851 0.05131 -0.0849 0.1759 1.0000
13.250 1.4184 0.06190 0.05468 -0.0843 0.1605 1.0000
13.500 1.4142 0.06539 0.05815 -0.0838 0.1461 1.0000
13.750 1.4104 0.06894 0.06171 -0.0835 0.1327 1.0000
14.000 1.4069 0.07256 0.06536 -0.0834 0.1203 1.0000
14.250 1.4037 0.07623 0.06907 -0.0834 0.1090 1.0000
14.500 1.4006 0.07999 0.07286 -0.0835 0.0989 1.0000
14.750 1.3964 0.08396 0.07685 -0.0838 0.0901 1.0000
15.000 1.3928 0.08797 0.08090 -0.0842 0.0818 1.0000
15.250 1.3904 0.09187 0.08488 -0.0847 0.0744 1.0000
15.500 1.3851 0.09626 0.08927 -0.0855 0.0685 1.0000
15.750 1.3836 0.10014 0.09329 -0.0862 0.0622 1.0000
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