EPPLER 421 AIRFOIL (e421-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 421 AIRFOIL (e421-il) Reynolds number: 1,000,000 Max Cl/Cd: 141.28 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e421-il-1000000-n5.txt Download as CSV file: xf-e421-il-1000000-n5.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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-19.250 -0.0453 0.16465 0.16288 -0.0728 0.9788 0.0084
-19.000 -0.0362 0.16235 0.16058 -0.0750 0.9766 0.0084
-18.500 -0.1880 0.19313 0.19117 -0.0565 0.9882 0.0084
-11.000 0.0379 0.07426 0.07028 -0.1349 0.5849 0.0071
-10.750 -0.0012 0.06555 0.06150 -0.1389 0.5833 0.0071
-10.500 -0.0160 0.06083 0.05672 -0.1409 0.5789 0.0070
-10.250 -0.0356 0.05604 0.05190 -0.1427 0.5746 0.0070
-10.000 -0.0613 0.05178 0.04763 -0.1433 0.5712 0.0070
-9.750 -0.0828 0.04535 0.04116 -0.1494 0.5680 0.0072
-9.500 -0.0996 0.03489 0.03048 -0.1640 0.5648 0.0069
-9.250 -0.0973 0.02120 0.01621 -0.1806 0.5611 0.0070
-9.000 -0.0744 0.01860 0.01336 -0.1825 0.5550 0.0070
-8.750 -0.0493 0.01740 0.01201 -0.1832 0.5497 0.0071
-8.500 -0.0237 0.01652 0.01100 -0.1835 0.5437 0.0073
-8.250 0.0019 0.01579 0.01013 -0.1836 0.5376 0.0074
-8.000 0.0283 0.01518 0.00941 -0.1837 0.5329 0.0075
-7.750 0.0549 0.01462 0.00874 -0.1838 0.5284 0.0077
-7.500 0.0816 0.01414 0.00816 -0.1837 0.5235 0.0078
-7.250 0.1082 0.01372 0.00764 -0.1836 0.5188 0.0080
-7.000 0.1354 0.01335 0.00717 -0.1836 0.5151 0.0082
-6.750 0.1627 0.01298 0.00672 -0.1835 0.5113 0.0083
-6.500 0.1901 0.01269 0.00635 -0.1834 0.5069 0.0084
-6.250 0.2171 0.01233 0.00590 -0.1832 0.5024 0.0087
-6.000 0.2443 0.01203 0.00551 -0.1831 0.4984 0.0090
-5.750 0.2721 0.01177 0.00521 -0.1830 0.4953 0.0093
-5.500 0.2998 0.01154 0.00492 -0.1829 0.4919 0.0097
-5.250 0.3274 0.01135 0.00466 -0.1827 0.4886 0.0101
-5.000 0.3550 0.01118 0.00443 -0.1825 0.4852 0.0105
-4.750 0.3824 0.01104 0.00422 -0.1823 0.4817 0.0110
-4.500 0.4104 0.01085 0.00400 -0.1822 0.4795 0.0118
-4.250 0.4383 0.01070 0.00382 -0.1821 0.4769 0.0127
-4.000 0.4661 0.01057 0.00365 -0.1819 0.4737 0.0139
-3.750 0.4938 0.01045 0.00350 -0.1818 0.4705 0.0158
-3.500 0.5213 0.01035 0.00337 -0.1816 0.4675 0.0184
-3.250 0.5488 0.01026 0.00325 -0.1813 0.4645 0.0218
-3.000 0.5766 0.01014 0.00314 -0.1812 0.4626 0.0272
-2.750 0.6045 0.01004 0.00305 -0.1811 0.4607 0.0336
-2.500 0.6323 0.00994 0.00297 -0.1810 0.4585 0.0412
-2.250 0.6600 0.00987 0.00291 -0.1808 0.4559 0.0496
-2.000 0.6874 0.00982 0.00286 -0.1806 0.4533 0.0579
-1.750 0.7148 0.00978 0.00283 -0.1804 0.4507 0.0667
-1.500 0.7419 0.00976 0.00282 -0.1802 0.4481 0.0773
-1.250 0.7693 0.00974 0.00281 -0.1800 0.4461 0.0873
-1.000 0.7970 0.00972 0.00280 -0.1798 0.4446 0.0956
-0.750 0.8245 0.00971 0.00280 -0.1796 0.4428 0.1044
-0.500 0.8520 0.00970 0.00282 -0.1794 0.4408 0.1135
-0.250 0.8792 0.00971 0.00283 -0.1792 0.4385 0.1211
0.000 0.9062 0.00974 0.00286 -0.1790 0.4362 0.1293
0.250 0.9331 0.00978 0.00290 -0.1787 0.4342 0.1375
0.500 0.9597 0.00983 0.00295 -0.1784 0.4320 0.1452
0.750 0.9860 0.00989 0.00301 -0.1780 0.4297 0.1539
1.000 1.0133 0.00992 0.00306 -0.1778 0.4285 0.1614
1.250 1.0403 0.00995 0.00311 -0.1776 0.4268 0.1688
1.500 1.0671 0.00999 0.00316 -0.1773 0.4250 0.1767
1.750 1.0937 0.01004 0.00322 -0.1770 0.4232 0.1833
2.000 1.1201 0.01010 0.00330 -0.1767 0.4214 0.1919
2.250 1.1462 0.01017 0.00337 -0.1764 0.4195 0.1986
2.500 1.1720 0.01025 0.00346 -0.1759 0.4176 0.2071
2.750 1.1974 0.01034 0.00356 -0.1755 0.4153 0.2147
3.000 1.2225 0.01045 0.00366 -0.1749 0.4131 0.2231
3.250 1.2487 0.01049 0.00375 -0.1746 0.4118 0.2323
3.500 1.2745 0.01056 0.00385 -0.1742 0.4104 0.2422
3.750 1.2997 0.01062 0.00395 -0.1737 0.4089 0.2543
4.000 1.3244 0.01069 0.00405 -0.1732 0.4072 0.2662
4.250 1.3486 0.01076 0.00417 -0.1725 0.4052 0.2817
4.500 1.3725 0.01084 0.00429 -0.1718 0.4033 0.3006
4.750 1.3957 0.01095 0.00443 -0.1710 0.4011 0.3211
5.000 1.4188 0.01106 0.00458 -0.1702 0.3991 0.3469
5.250 1.4417 0.01118 0.00477 -0.1693 0.3970 0.3863
5.500 1.4663 0.01120 0.00495 -0.1689 0.3958 0.4503
6.000 1.5137 0.01073 0.00541 -0.1677 0.3921 1.0000
6.250 1.5370 0.01088 0.00556 -0.1669 0.3900 1.0000
6.500 1.5597 0.01104 0.00572 -0.1661 0.3876 1.0000
6.750 1.5817 0.01123 0.00590 -0.1651 0.3849 1.0000
7.000 1.6027 0.01145 0.00611 -0.1640 0.3819 1.0000
7.250 1.6257 0.01161 0.00628 -0.1633 0.3796 1.0000
7.500 1.6483 0.01177 0.00646 -0.1625 0.3767 1.0000
7.750 1.6702 0.01196 0.00666 -0.1616 0.3736 1.0000
8.000 1.6910 0.01219 0.00689 -0.1606 0.3704 1.0000
8.250 1.7106 0.01246 0.00715 -0.1593 0.3669 1.0000
8.500 1.7317 0.01268 0.00739 -0.1583 0.3642 1.0000
8.750 1.7529 0.01289 0.00763 -0.1574 0.3611 1.0000
9.000 1.7732 0.01314 0.00789 -0.1563 0.3579 1.0000
9.250 1.7917 0.01346 0.00821 -0.1550 0.3539 1.0000
9.500 1.8094 0.01380 0.00856 -0.1536 0.3502 1.0000
9.750 1.8290 0.01408 0.00887 -0.1525 0.3459 1.0000
10.000 1.8467 0.01444 0.00924 -0.1511 0.3412 1.0000
10.250 1.8611 0.01493 0.00972 -0.1492 0.3361 1.0000
10.500 1.8794 0.01528 0.01010 -0.1480 0.3319 1.0000
10.750 1.8946 0.01576 0.01059 -0.1464 0.3265 1.0000
11.000 1.9073 0.01637 0.01120 -0.1445 0.3212 1.0000
11.250 1.9221 0.01690 0.01175 -0.1429 0.3153 1.0000
11.500 1.9324 0.01766 0.01251 -0.1408 0.3085 1.0000
11.750 1.9445 0.01837 0.01324 -0.1390 0.3026 1.0000
12.000 1.9544 0.01922 0.01410 -0.1370 0.2962 1.0000
12.250 1.9611 0.02029 0.01517 -0.1347 0.2880 1.0000
12.500 1.9650 0.02158 0.01645 -0.1323 0.2793 1.0000
12.750 1.9689 0.02295 0.01783 -0.1300 0.2698 1.0000
13.000 1.9693 0.02465 0.01953 -0.1276 0.2609 1.0000
13.250 1.9673 0.02663 0.02150 -0.1252 0.2510 1.0000
13.500 1.9646 0.02879 0.02367 -0.1230 0.2410 1.0000
13.750 1.9590 0.03132 0.02620 -0.1208 0.2323 1.0000
14.000 1.9503 0.03426 0.02914 -0.1187 0.2228 1.0000
14.250 1.9399 0.03749 0.03239 -0.1168 0.2124 1.0000
14.500 1.9292 0.04093 0.03585 -0.1152 0.2048 1.0000
14.750 1.9185 0.04452 0.03947 -0.1138 0.1971 1.0000
15.000 1.9070 0.04829 0.04328 -0.1126 0.1900 1.0000
15.250 1.8966 0.05210 0.04713 -0.1116 0.1837 1.0000
15.500 1.8850 0.05616 0.05123 -0.1107 0.1778 1.0000
15.750 1.8738 0.06027 0.05538 -0.1101 0.1714 1.0000
16.000 1.8596 0.06484 0.05999 -0.1096 0.1651 1.0000
16.250 1.8490 0.06911 0.06430 -0.1093 0.1590 1.0000
16.500 1.8354 0.07381 0.06904 -0.1091 0.1534 1.0000
16.750 1.8284 0.07776 0.07304 -0.1091 0.1478 1.0000
17.000 1.8159 0.08250 0.07781 -0.1092 0.1421 1.0000
17.250 1.8084 0.08669 0.08204 -0.1094 0.1369 1.0000
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