EPPLER 421 AIRFOIL (e421-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 421 AIRFOIL (e421-il) Reynolds number: 200,000 Max Cl/Cd: 62.96 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e421-il-200000.txt Download as CSV file: xf-e421-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 421 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
------ -------- --------- --------- -------- -------- --------
-9.750 0.2215 0.09614 0.09176 -0.1297 0.7926 0.0447
-9.500 0.2343 0.09396 0.08941 -0.1303 0.7708 0.0452
-9.250 0.2440 0.09197 0.08729 -0.1305 0.7532 0.0464
-9.000 0.2522 0.09004 0.08526 -0.1309 0.7386 0.0471
-8.750 0.2569 0.08807 0.08319 -0.1318 0.7268 0.0491
-8.500 0.2426 0.08688 0.08203 -0.1349 0.7164 0.0499
-8.250 0.2644 0.08372 0.07873 -0.1335 0.7060 0.0504
-8.000 0.2772 0.08165 0.07664 -0.1329 0.6954 0.0512
-7.750 0.2871 0.07976 0.07465 -0.1331 0.6872 0.0525
-7.500 0.2931 0.07783 0.07274 -0.1334 0.6783 0.0543
-7.250 0.2817 0.07631 0.07122 -0.1360 0.6716 0.0562
-7.000 0.2902 0.07361 0.06849 -0.1358 0.6647 0.0568
-6.750 0.3049 0.07152 0.06638 -0.1349 0.6569 0.0575
-6.500 0.3166 0.06978 0.06457 -0.1344 0.6506 0.0595
-6.250 0.3178 0.06812 0.06293 -0.1346 0.6448 0.0620
-6.000 0.3064 0.06536 0.06024 -0.1416 0.6398 0.0637
-5.750 0.3270 0.06415 0.05897 -0.1358 0.6338 0.0657
-5.500 0.3393 0.06230 0.05704 -0.1367 0.6290 0.0677
-5.250 0.3473 0.05787 0.05264 -0.1490 0.6245 0.0720
-5.000 0.3590 0.05636 0.05114 -0.1452 0.6190 0.0729
-4.750 0.3747 0.04765 0.04231 -0.1555 0.6157 0.0559
-4.500 0.3934 0.04699 0.04156 -0.1547 0.6110 0.0583
-4.250 0.4371 0.02037 0.01225 -0.1828 0.6101 0.0444
-4.000 0.4624 0.01993 0.01181 -0.1824 0.6047 0.0491
-3.750 0.4893 0.01941 0.01121 -0.1823 0.5998 0.0549
-3.500 0.5174 0.01892 0.01056 -0.1824 0.5956 0.0629
-3.250 0.5465 0.01869 0.01023 -0.1826 0.5918 0.0734
-3.000 0.5726 0.01859 0.01018 -0.1823 0.5876 0.0843
-2.750 0.5993 0.01856 0.01014 -0.1821 0.5831 0.0960
-2.500 0.6269 0.01852 0.01005 -0.1819 0.5790 0.1077
-2.250 0.6554 0.01849 0.00990 -0.1819 0.5754 0.1195
-2.000 0.6842 0.01863 0.00989 -0.1820 0.5719 0.1314
-1.750 0.7096 0.01866 0.01002 -0.1815 0.5682 0.1421
-1.500 0.7362 0.01863 0.01000 -0.1812 0.5645 0.1528
-1.250 0.7639 0.01865 0.00990 -0.1811 0.5612 0.1647
-1.000 0.7919 0.01872 0.00995 -0.1810 0.5580 0.1761
-0.750 0.8210 0.01878 0.00990 -0.1812 0.5550 0.1875
-0.500 0.8472 0.01897 0.01002 -0.1808 0.5518 0.1992
-0.250 0.8723 0.01895 0.01011 -0.1803 0.5484 0.2098
0.000 0.8988 0.01901 0.01012 -0.1801 0.5453 0.2215
0.250 0.9258 0.01910 0.01021 -0.1799 0.5424 0.2332
0.500 0.9538 0.01913 0.01019 -0.1799 0.5397 0.2447
0.750 0.9830 0.01931 0.01024 -0.1801 0.5371 0.2576
1.000 1.0094 0.01946 0.01045 -0.1799 0.5343 0.2696
1.250 1.0331 0.01957 0.01064 -0.1792 0.5313 0.2818
1.500 1.0581 0.01976 0.01085 -0.1787 0.5283 0.2952
1.750 1.0838 0.01987 0.01103 -0.1784 0.5256 0.3094
2.000 1.1107 0.01998 0.01117 -0.1783 0.5230 0.3251
2.250 1.1387 0.02009 0.01128 -0.1784 0.5206 0.3437
2.500 1.1680 0.02029 0.01146 -0.1787 0.5182 0.3668
2.750 1.1920 0.02052 0.01184 -0.1782 0.5157 0.3938
3.000 1.2138 0.02066 0.01223 -0.1773 0.5129 0.4370
3.250 1.2356 0.02003 0.01257 -0.1761 0.5102 1.0000
3.500 1.2605 0.02038 0.01284 -0.1757 0.5076 1.0000
3.750 1.2865 0.02069 0.01306 -0.1754 0.5050 1.0000
4.000 1.3143 0.02097 0.01325 -0.1754 0.5027 1.0000
4.250 1.3436 0.02134 0.01350 -0.1758 0.5005 1.0000
4.500 1.3682 0.02190 0.01404 -0.1755 0.4983 1.0000
4.750 1.3870 0.02240 0.01463 -0.1741 0.4957 1.0000
5.000 1.4073 0.02288 0.01516 -0.1730 0.4928 1.0000
5.250 1.4297 0.02329 0.01558 -0.1722 0.4899 1.0000
5.500 1.4543 0.02363 0.01591 -0.1718 0.4874 1.0000
5.750 1.4805 0.02397 0.01621 -0.1716 0.4852 1.0000
6.000 1.5091 0.02435 0.01653 -0.1720 0.4832 1.0000
6.250 1.5364 0.02494 0.01709 -0.1722 0.4811 1.0000
6.500 1.5479 0.02560 0.01791 -0.1697 0.4780 1.0000
6.750 1.5642 0.02621 0.01861 -0.1680 0.4749 1.0000
7.000 1.5838 0.02673 0.01918 -0.1669 0.4721 1.0000
7.250 1.6074 0.02708 0.01955 -0.1664 0.4695 1.0000
7.500 1.6341 0.02735 0.01979 -0.1664 0.4672 1.0000
7.750 1.6651 0.02764 0.02002 -0.1672 0.4651 1.0000
8.000 1.6818 0.02839 0.02087 -0.1657 0.4624 1.0000
8.250 1.6864 0.02926 0.02191 -0.1622 0.4586 1.0000
8.500 1.7001 0.02987 0.02261 -0.1603 0.4553 1.0000
8.750 1.7222 0.03015 0.02292 -0.1595 0.4524 1.0000
9.000 1.7504 0.03026 0.02300 -0.1598 0.4499 1.0000
9.250 1.7864 0.03030 0.02297 -0.1613 0.4476 1.0000
9.500 1.7888 0.03131 0.02416 -0.1577 0.4441 1.0000
9.750 1.7845 0.03237 0.02538 -0.1530 0.4401 1.0000
10.000 1.7953 0.03284 0.02592 -0.1505 0.4367 1.0000
10.250 1.8218 0.03284 0.02593 -0.1504 0.4339 1.0000
10.500 1.8626 0.03257 0.02560 -0.1527 0.4313 1.0000
10.750 1.8741 0.03325 0.02635 -0.1505 0.4282 1.0000
11.000 1.8387 0.03508 0.02842 -0.1414 0.4238 1.0000
11.250 1.8411 0.03586 0.02928 -0.1381 0.4200 1.0000
11.500 1.8701 0.03561 0.02903 -0.1383 0.4170 1.0000
11.750 1.9248 0.03460 0.02793 -0.1421 0.4142 1.0000
12.000 1.8934 0.03672 0.03027 -0.1345 0.4100 1.0000
12.250 1.8546 0.03959 0.03334 -0.1272 0.4049 1.0000
12.500 1.8786 0.03938 0.03316 -0.1267 0.4014 1.0000
12.750 1.9359 0.03759 0.03128 -0.1298 0.3985 1.0000
13.000 1.8984 0.04081 0.03470 -0.1234 0.3936 1.0000
13.250 1.8484 0.04548 0.03957 -0.1174 0.3874 1.0000
13.500 1.8926 0.04377 0.03784 -0.1183 0.3844 1.0000
13.750 1.9638 0.04063 0.03458 -0.1218 0.3815 1.0000
14.000 1.8093 0.05421 0.04859 -0.1109 0.3713 1.0000
14.250 1.8696 0.05051 0.04486 -0.1119 0.3690 1.0000
14.500 1.9407 0.04636 0.04061 -0.1139 0.3663 1.0000
14.750 1.7005 0.07345 0.06816 -0.1070 0.3464 1.0000
15.000 1.7739 0.06690 0.06160 -0.1067 0.3467 1.0000
15.250 1.7695 0.06986 0.06463 -0.1062 0.3400 1.0000
15.500 1.8355 0.06443 0.05917 -0.1060 0.3382 1.0000
15.750 1.7557 0.07681 0.07171 -0.1055 0.3256 1.0000
16.000 1.8161 0.07168 0.06655 -0.1050 0.3235 1.0000
16.250 1.7570 0.08208 0.07709 -0.1052 0.3115 1.0000
16.500 1.8120 0.07744 0.07241 -0.1044 0.3086 1.0000
16.750 1.7647 0.08663 0.08172 -0.1050 0.2971 1.0000
17.000 1.8183 0.08204 0.07706 -0.1041 0.2934 1.0000
17.250 1.7733 0.09116 0.08631 -0.1049 0.2820 1.0000
17.500 1.7873 0.09204 0.08719 -0.1047 0.2750 1.0000
17.750 1.7849 0.09528 0.09044 -0.1049 0.2664 1.0000
18.000 1.7712 0.10025 0.09548 -0.1055 0.2572 1.0000
18.250 1.7988 0.09903 0.09416 -0.1049 0.2504 1.0000
18.500 1.7711 0.10621 0.10146 -0.1062 0.2407 1.0000
18.750 1.7834 0.10725 0.10246 -0.1061 0.2332 1.0000
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