EPPLER 421 AIRFOIL (e421-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 421 AIRFOIL (e421-il) Reynolds number: 500,000 Max Cl/Cd: 109.93 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e421-il-500000-n5.txt Download as CSV file: xf-e421-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 0.1938 0.08800 0.08338 -0.1276 0.5913 0.0105
-8.750 0.0218 0.05014 0.04555 -0.1402 0.5869 0.0098
-8.500 -0.0062 0.03894 0.03413 -0.1541 0.5841 0.0098
-8.250 0.0026 0.02860 0.02338 -0.1691 0.5794 0.0098
-8.000 0.0252 0.02284 0.01722 -0.1759 0.5740 0.0099
-7.750 0.0504 0.02057 0.01469 -0.1780 0.5686 0.0101
-7.500 0.0758 0.01925 0.01316 -0.1789 0.5625 0.0103
-7.250 0.1012 0.01828 0.01199 -0.1793 0.5564 0.0105
-7.000 0.1272 0.01749 0.01102 -0.1795 0.5512 0.0107
-6.750 0.1536 0.01671 0.01011 -0.1798 0.5460 0.0109
-6.500 0.1798 0.01604 0.00931 -0.1799 0.5410 0.0113
-6.250 0.2061 0.01554 0.00867 -0.1798 0.5364 0.0116
-6.000 0.2332 0.01507 0.00810 -0.1799 0.5324 0.0119
-5.750 0.2603 0.01467 0.00760 -0.1798 0.5282 0.0124
-5.500 0.2873 0.01430 0.00711 -0.1797 0.5237 0.0129
-5.250 0.3142 0.01400 0.00668 -0.1795 0.5194 0.0134
-5.000 0.3414 0.01365 0.00625 -0.1794 0.5155 0.0141
-4.750 0.3690 0.01338 0.00591 -0.1793 0.5117 0.0153
-4.500 0.3964 0.01313 0.00559 -0.1792 0.5080 0.0166
-4.250 0.4236 0.01292 0.00532 -0.1790 0.5044 0.0185
-4.000 0.4507 0.01272 0.00504 -0.1788 0.5010 0.0210
-3.750 0.4781 0.01254 0.00481 -0.1786 0.4981 0.0244
-3.500 0.5059 0.01236 0.00461 -0.1785 0.4953 0.0288
-3.250 0.5334 0.01221 0.00444 -0.1783 0.4922 0.0349
-3.000 0.5607 0.01209 0.00430 -0.1781 0.4888 0.0418
-2.750 0.5878 0.01201 0.00419 -0.1779 0.4856 0.0494
-2.500 0.6147 0.01195 0.00410 -0.1776 0.4826 0.0572
-2.250 0.6421 0.01188 0.00403 -0.1774 0.4802 0.0662
-2.000 0.6697 0.01181 0.00398 -0.1773 0.4779 0.0761
-1.750 0.6972 0.01176 0.00395 -0.1771 0.4754 0.0861
-1.500 0.7245 0.01174 0.00392 -0.1769 0.4729 0.0949
-1.250 0.7515 0.01174 0.00390 -0.1766 0.4702 0.1041
-1.000 0.7782 0.01175 0.00390 -0.1763 0.4674 0.1136
-0.750 0.8048 0.01179 0.00392 -0.1759 0.4649 0.1222
-0.500 0.8318 0.01183 0.00393 -0.1757 0.4628 0.1305
-0.250 0.8591 0.01183 0.00397 -0.1755 0.4609 0.1397
0.000 0.8862 0.01186 0.00399 -0.1752 0.4588 0.1478
0.250 0.9131 0.01190 0.00405 -0.1750 0.4566 0.1570
0.500 0.9396 0.01195 0.00409 -0.1746 0.4542 0.1648
0.750 0.9660 0.01201 0.00415 -0.1743 0.4519 0.1735
1.000 0.9920 0.01210 0.00420 -0.1739 0.4495 0.1809
1.250 1.0179 0.01219 0.00429 -0.1735 0.4475 0.1896
1.500 1.0443 0.01227 0.00437 -0.1732 0.4457 0.1978
1.750 1.0709 0.01232 0.00446 -0.1729 0.4440 0.2060
2.000 1.0972 0.01239 0.00455 -0.1726 0.4420 0.2151
2.250 1.1232 0.01246 0.00464 -0.1722 0.4398 0.2230
2.500 1.1489 0.01254 0.00474 -0.1718 0.4376 0.2331
2.750 1.1744 0.01264 0.00485 -0.1714 0.4356 0.2426
3.000 1.1995 0.01275 0.00497 -0.1709 0.4337 0.2542
3.250 1.2244 0.01286 0.00511 -0.1704 0.4319 0.2671
3.500 1.2491 0.01301 0.00526 -0.1698 0.4299 0.2807
3.750 1.2745 0.01309 0.00541 -0.1694 0.4282 0.2989
4.000 1.2995 0.01316 0.00556 -0.1689 0.4264 0.3206
4.250 1.3239 0.01324 0.00571 -0.1683 0.4244 0.3461
4.500 1.3479 0.01332 0.00589 -0.1677 0.4225 0.3825
4.750 1.3716 0.01335 0.00608 -0.1671 0.4206 0.4542
5.250 1.4166 0.01296 0.00653 -0.1653 0.4167 1.0000
5.500 1.4388 0.01317 0.00671 -0.1643 0.4147 1.0000
5.750 1.4615 0.01339 0.00691 -0.1635 0.4127 1.0000
6.000 1.4848 0.01355 0.00710 -0.1627 0.4111 1.0000
6.250 1.5078 0.01373 0.00731 -0.1620 0.4093 1.0000
6.500 1.5302 0.01392 0.00752 -0.1611 0.4072 1.0000
6.750 1.5521 0.01412 0.00773 -0.1602 0.4049 1.0000
7.000 1.5736 0.01434 0.00796 -0.1592 0.4027 1.0000
7.250 1.5944 0.01458 0.00820 -0.1581 0.4005 1.0000
7.500 1.6144 0.01485 0.00846 -0.1569 0.3982 1.0000
7.750 1.6351 0.01511 0.00873 -0.1559 0.3959 1.0000
8.000 1.6561 0.01532 0.00901 -0.1549 0.3933 1.0000
8.250 1.6761 0.01557 0.00930 -0.1537 0.3903 1.0000
8.500 1.6952 0.01585 0.00960 -0.1525 0.3873 1.0000
8.750 1.7132 0.01617 0.00993 -0.1511 0.3843 1.0000
9.000 1.7302 0.01655 0.01030 -0.1495 0.3815 1.0000
9.250 1.7496 0.01684 0.01066 -0.1484 0.3786 1.0000
9.500 1.7680 0.01717 0.01105 -0.1472 0.3754 1.0000
9.750 1.7848 0.01756 0.01147 -0.1457 0.3720 1.0000
10.000 1.8004 0.01801 0.01194 -0.1441 0.3688 1.0000
10.250 1.8149 0.01852 0.01246 -0.1424 0.3656 1.0000
10.500 1.8320 0.01894 0.01297 -0.1411 0.3620 1.0000
10.750 1.8467 0.01947 0.01355 -0.1396 0.3579 1.0000
11.000 1.8591 0.02012 0.01422 -0.1378 0.3537 1.0000
11.250 1.8710 0.02082 0.01495 -0.1360 0.3497 1.0000
11.500 1.8845 0.02148 0.01568 -0.1345 0.3450 1.0000
11.750 1.8952 0.02232 0.01656 -0.1327 0.3403 1.0000
12.000 1.9031 0.02334 0.01760 -0.1307 0.3357 1.0000
12.250 1.9144 0.02423 0.01857 -0.1292 0.3305 1.0000
12.500 1.9208 0.02545 0.01983 -0.1273 0.3247 1.0000
12.750 1.9265 0.02679 0.02121 -0.1255 0.3191 1.0000
13.000 1.9323 0.02819 0.02266 -0.1238 0.3127 1.0000
13.250 1.9325 0.03007 0.02456 -0.1218 0.3065 1.0000
13.500 1.9363 0.03179 0.02634 -0.1203 0.2993 1.0000
13.750 1.9322 0.03423 0.02880 -0.1184 0.2921 1.0000
14.000 1.9307 0.03656 0.03118 -0.1169 0.2834 1.0000
14.250 1.9243 0.03944 0.03409 -0.1153 0.2758 1.0000
14.500 1.9150 0.04274 0.03742 -0.1138 0.2664 1.0000
14.750 1.9059 0.04615 0.04087 -0.1125 0.2580 1.0000
15.000 1.8899 0.05041 0.04516 -0.1112 0.2490 1.0000
15.250 1.8774 0.05446 0.04925 -0.1102 0.2396 1.0000
15.500 1.8625 0.05890 0.05372 -0.1094 0.2312 1.0000
15.750 1.8447 0.06383 0.05867 -0.1088 0.2225 1.0000
16.000 1.8327 0.06820 0.06309 -0.1084 0.2143 1.0000
16.250 1.8157 0.07328 0.06819 -0.1082 0.2066 1.0000
16.500 1.8047 0.07772 0.07267 -0.1081 0.1988 1.0000
16.750 1.7909 0.08262 0.07760 -0.1082 0.1917 1.0000
17.000 1.7813 0.08701 0.08202 -0.1084 0.1842 1.0000
17.250 1.7709 0.09158 0.08662 -0.1087 0.1779 1.0000
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Polar data table (+)
Polar graphs
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