EPPLER 421 AIRFOIL (e421-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: EPPLER 421 AIRFOIL (e421-il) Reynolds number: 100,000 Max Cl/Cd: 27.66 at α=1° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e421-il-100000.txt Download as CSV file: xf-e421-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 0.0505 0.12343 0.11895 -0.0861 0.9253 0.0684
-10.250 0.0709 0.11986 0.11536 -0.0918 0.9140 0.0708
-10.000 0.0794 0.11907 0.11454 -0.1010 0.9019 0.0718
-9.750 0.1283 0.11023 0.10562 -0.1037 0.8946 0.0744
-9.500 0.1596 0.10591 0.10121 -0.1100 0.8817 0.0772
-9.250 0.1743 0.10455 0.09974 -0.1191 0.8658 0.0808
-9.000 0.2063 0.09895 0.09401 -0.1233 0.8509 0.0820
-8.750 0.2369 0.09474 0.08964 -0.1264 0.8350 0.0851
-8.500 0.2549 0.09214 0.08691 -0.1299 0.8197 0.0888
-8.250 0.2539 0.09224 0.08691 -0.1341 0.8045 0.0911
-8.000 0.2588 0.09003 0.08467 -0.1351 0.7902 0.0919
-7.750 0.2863 0.08552 0.08005 -0.1344 0.7789 0.0939
-7.500 0.2997 0.08330 0.07774 -0.1348 0.7678 0.0967
-7.250 0.3053 0.08181 0.07623 -0.1352 0.7572 0.0999
-7.000 0.2928 0.08238 0.07680 -0.1372 0.7481 0.1026
-6.750 0.2821 0.08209 0.07658 -0.1382 0.7391 0.1033
-6.500 0.3191 0.07642 0.07079 -0.1360 0.7314 0.1058
-6.250 0.3314 0.07443 0.06874 -0.1357 0.7245 0.1086
-6.000 0.3304 0.07341 0.06778 -0.1346 0.7162 0.1119
-5.750 0.3211 0.07420 0.06856 -0.1419 0.7097 0.1159
-5.500 0.3332 0.07062 0.06498 -0.1393 0.7037 0.1174
-5.250 0.3465 0.06845 0.06284 -0.1358 0.6969 0.1208
-5.000 0.3571 0.06695 0.06129 -0.1374 0.6914 0.1272
-4.750 0.3699 0.06473 0.05899 -0.1444 0.6870 0.1319
-4.500 0.3758 0.06300 0.05737 -0.1403 0.6806 0.1342
-4.250 0.3885 0.06123 0.05559 -0.1401 0.6750 0.1382
-4.000 0.4166 0.05845 0.05261 -0.1520 0.6704 0.1471
-3.750 0.4469 0.04878 0.04262 -0.1626 0.6671 0.1023
-3.500 0.4610 0.04625 0.04010 -0.1632 0.6611 0.1009
-3.250 0.4928 0.04030 0.03380 -0.1700 0.6566 0.0982
-3.000 0.5295 0.03524 0.02812 -0.1758 0.6528 0.1069
-2.750 0.5626 0.03345 0.02590 -0.1779 0.6494 0.1198
-2.500 0.5845 0.03230 0.02440 -0.1781 0.6444 0.1321
-2.250 0.6047 0.03256 0.02470 -0.1769 0.6391 0.1432
-2.000 0.6305 0.03231 0.02438 -0.1766 0.6348 0.1552
-1.750 0.6618 0.03159 0.02337 -0.1774 0.6314 0.1694
-1.500 0.6883 0.03123 0.02270 -0.1776 0.6279 0.1834
-1.250 0.7013 0.03184 0.02346 -0.1755 0.6229 0.1927
-1.000 0.7243 0.03176 0.02322 -0.1751 0.6187 0.2053
-0.750 0.7526 0.03156 0.02276 -0.1752 0.6151 0.2205
-0.500 0.7834 0.03140 0.02247 -0.1756 0.6121 0.2355
-0.250 0.8036 0.03176 0.02283 -0.1747 0.6085 0.2471
0.000 0.8112 0.03285 0.02388 -0.1722 0.6035 0.2577
0.250 0.8278 0.03340 0.02452 -0.1708 0.5996 0.2690
0.500 0.8550 0.03346 0.02447 -0.1708 0.5964 0.2835
0.750 0.8867 0.03336 0.02423 -0.1713 0.5938 0.3000
1.000 0.9209 0.03329 0.02401 -0.1721 0.5914 0.3177
1.250 0.8879 0.03678 0.02784 -0.1648 0.5843 0.3176
1.500 0.8901 0.03846 0.02959 -0.1620 0.5799 0.3272
1.750 0.9183 0.03859 0.02967 -0.1620 0.5771 0.3442
2.000 0.9563 0.03821 0.02920 -0.1632 0.5751 0.3662
2.250 0.9966 0.03778 0.02871 -0.1647 0.5733 0.3912
2.500 0.7817 0.05568 0.04711 -0.1437 0.5561 0.3324
2.750 0.8352 0.05337 0.04479 -0.1446 0.5553 0.3587
3.000 0.8932 0.05112 0.04246 -0.1465 0.5548 0.3909
3.250 0.9552 0.04883 0.04016 -0.1492 0.5543 0.4333
4.250 0.7621 0.08025 0.07194 -0.1375 0.5351 0.3974
4.500 0.7726 0.08326 0.07501 -0.1376 0.5355 0.4166
6.000 0.6938 0.10888 0.10129 -0.1360 0.5445 0.4845
6.250 0.7158 0.10939 0.10258 -0.1355 0.5399 1.0000
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Polar data table (+)
Polar graphs
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