EPPLER 421 AIRFOIL (e421-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: EPPLER 421 AIRFOIL (e421-il) Reynolds number: 100,000 Max Cl/Cd: 48.01 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e421-il-100000-n5.txt Download as CSV file: xf-e421-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 0.1863 0.10092 0.09487 -0.1160 0.7502 0.0542
-9.250 0.1896 0.09896 0.09286 -0.1184 0.7375 0.0561
-9.000 0.2000 0.09648 0.09029 -0.1201 0.7262 0.0561
-8.750 0.2039 0.09434 0.08813 -0.1217 0.7152 0.0563
-8.500 0.2119 0.09181 0.08553 -0.1231 0.7062 0.0563
-8.000 0.2336 0.08417 0.07775 -0.1240 0.6889 0.0381
-7.500 0.2362 0.07804 0.07160 -0.1262 0.6737 0.0342
-7.250 0.2444 0.07586 0.06936 -0.1266 0.6669 0.0339
-7.000 0.2492 0.07363 0.06716 -0.1267 0.6593 0.0336
-6.750 0.2525 0.07133 0.06485 -0.1269 0.6528 0.0333
-6.500 0.2536 0.06909 0.06257 -0.1270 0.6472 0.0331
-6.250 0.2561 0.06668 0.06020 -0.1277 0.6408 0.0329
-6.000 0.2601 0.06378 0.05730 -0.1293 0.6354 0.0329
-5.750 0.2668 0.06058 0.05405 -0.1319 0.6309 0.0330
-5.500 0.2719 0.05558 0.04903 -0.1371 0.6263 0.0339
-5.250 0.2854 0.05242 0.04586 -0.1406 0.6208 0.0349
-5.000 0.3029 0.04871 0.04207 -0.1451 0.6157 0.0362
-4.750 0.3412 0.02779 0.01942 -0.1720 0.6135 0.0390
-4.500 0.3681 0.02700 0.01848 -0.1726 0.6086 0.0415
-4.250 0.3946 0.02579 0.01699 -0.1733 0.6028 0.0456
-4.000 0.4221 0.02472 0.01561 -0.1738 0.5977 0.0505
-3.750 0.4504 0.02404 0.01468 -0.1742 0.5935 0.0568
-3.500 0.4781 0.02358 0.01404 -0.1745 0.5893 0.0642
-3.250 0.5045 0.02326 0.01363 -0.1744 0.5845 0.0727
-3.000 0.5316 0.02300 0.01326 -0.1744 0.5799 0.0822
-2.750 0.5594 0.02280 0.01290 -0.1744 0.5759 0.0926
-2.500 0.5882 0.02266 0.01255 -0.1746 0.5725 0.1036
-2.250 0.6132 0.02266 0.01257 -0.1741 0.5678 0.1135
-2.000 0.6394 0.02264 0.01252 -0.1738 0.5636 0.1234
-1.750 0.6666 0.02257 0.01231 -0.1737 0.5600 0.1342
-1.500 0.6947 0.02252 0.01206 -0.1736 0.5569 0.1462
-1.250 0.7230 0.02258 0.01207 -0.1737 0.5541 0.1563
-1.000 0.7474 0.02263 0.01209 -0.1731 0.5501 0.1670
-0.750 0.7727 0.02271 0.01211 -0.1726 0.5462 0.1783
-0.500 0.7987 0.02276 0.01213 -0.1723 0.5426 0.1884
-0.250 0.8260 0.02281 0.01203 -0.1721 0.5396 0.2005
0.000 0.8538 0.02288 0.01205 -0.1721 0.5371 0.2113
0.250 0.8805 0.02299 0.01208 -0.1719 0.5345 0.2226
0.500 0.9034 0.02319 0.01232 -0.1711 0.5309 0.2338
0.750 0.9274 0.02334 0.01249 -0.1705 0.5274 0.2444
1.000 0.9528 0.02350 0.01258 -0.1700 0.5243 0.2573
1.250 0.9789 0.02360 0.01268 -0.1697 0.5215 0.2691
1.500 1.0066 0.02373 0.01275 -0.1697 0.5192 0.2827
1.750 1.0348 0.02391 0.01284 -0.1698 0.5171 0.2977
2.000 1.0552 0.02426 0.01330 -0.1686 0.5138 0.3123
2.250 1.0770 0.02456 0.01368 -0.1677 0.5105 0.3285
2.500 1.1004 0.02481 0.01398 -0.1670 0.5075 0.3480
2.750 1.1254 0.02502 0.01422 -0.1666 0.5048 0.3726
3.000 1.1518 0.02517 0.01443 -0.1665 0.5025 0.4079
3.250 1.1791 0.02519 0.01465 -0.1666 0.5005 0.4835
3.750 1.2168 0.02549 0.01563 -0.1636 0.4949 1.0000
4.000 1.2356 0.02607 0.01620 -0.1623 0.4917 1.0000
4.250 1.2568 0.02657 0.01666 -0.1613 0.4888 1.0000
4.500 1.2800 0.02702 0.01705 -0.1607 0.4865 1.0000
4.750 1.3053 0.02742 0.01738 -0.1604 0.4844 1.0000
5.000 1.3331 0.02777 0.01763 -0.1605 0.4825 1.0000
5.250 1.3521 0.02840 0.01827 -0.1594 0.4800 1.0000
5.500 1.3598 0.02937 0.01936 -0.1565 0.4763 1.0000
5.750 1.3731 0.03017 0.02022 -0.1545 0.4732 1.0000
6.000 1.3901 0.03085 0.02093 -0.1531 0.4706 1.0000
6.250 1.4110 0.03137 0.02144 -0.1522 0.4683 1.0000
6.500 1.4367 0.03173 0.02176 -0.1521 0.4662 1.0000
6.750 1.4670 0.03198 0.02195 -0.1526 0.4644 1.0000
7.000 1.4588 0.03352 0.02368 -0.1477 0.4606 1.0000
7.250 1.4460 0.03522 0.02554 -0.1422 0.4567 1.0000
7.500 1.4499 0.03640 0.02678 -0.1393 0.4534 1.0000
7.750 1.4668 0.03704 0.02744 -0.1380 0.4509 1.0000
8.000 1.4923 0.03734 0.02773 -0.1378 0.4489 1.0000
8.250 1.5264 0.03735 0.02770 -0.1387 0.4473 1.0000
8.500 1.3867 0.04722 0.03806 -0.1233 0.4353 1.0000
8.750 1.4097 0.04753 0.03838 -0.1228 0.4332 1.0000
9.000 1.4415 0.04716 0.03800 -0.1228 0.4318 1.0000
9.250 1.4778 0.04653 0.03734 -0.1233 0.4306 1.0000
9.750 1.3778 0.06035 0.05147 -0.1162 0.4131 1.0000
10.750 1.2042 0.09534 0.08693 -0.1153 0.3620 1.0000
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Polar data table (+)
Polar graphs
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