E216 (10.4%) (e216-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: E216 (10.4%) (e216-il) Reynolds number: 200,000 Max Cl/Cd: 94.03 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e216-il-200000-n5.txt Download as CSV file: xf-e216-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E216 (10.4%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.2561 0.07702 0.07352 -0.0717 0.9636 0.0156
-7.000 -0.2598 0.04179 0.03785 -0.1160 0.9420 0.0143
-6.750 -0.2279 0.03288 0.02800 -0.1299 0.9355 0.0144
-6.500 -0.1885 0.02838 0.02281 -0.1369 0.9333 0.0145
-6.250 -0.1491 0.02547 0.01936 -0.1416 0.9318 0.0146
-6.000 -0.1108 0.02324 0.01678 -0.1452 0.9305 0.0149
-5.750 -0.0730 0.02164 0.01497 -0.1482 0.9293 0.0153
-5.500 -0.0350 0.02040 0.01355 -0.1510 0.9282 0.0159
-5.250 -0.0084 0.01952 0.01255 -0.1513 0.9227 0.0165
-5.000 0.0267 0.01861 0.01150 -0.1532 0.9199 0.0173
-4.750 0.0634 0.01785 0.01060 -0.1553 0.9178 0.0187
-4.500 0.1013 0.01711 0.00981 -0.1578 0.9161 0.0211
-4.250 0.1403 0.01641 0.00896 -0.1603 0.9147 0.0232
-4.000 0.1708 0.01590 0.00840 -0.1612 0.9098 0.0264
-3.750 0.2053 0.01535 0.00781 -0.1627 0.9061 0.0356
-3.500 0.2429 0.01468 0.00730 -0.1650 0.9037 0.0710
-3.250 0.2805 0.01414 0.00690 -0.1673 0.9017 0.1148
-3.000 0.3190 0.01360 0.00657 -0.1698 0.9001 0.1755
-2.750 0.3462 0.01341 0.00644 -0.1698 0.8931 0.2112
-2.500 0.3809 0.01310 0.00617 -0.1712 0.8893 0.2482
-2.250 0.4184 0.01274 0.00589 -0.1732 0.8866 0.2890
-2.000 0.4498 0.01254 0.00574 -0.1739 0.8809 0.3251
-1.750 0.4827 0.01232 0.00557 -0.1748 0.8753 0.3589
-1.500 0.5209 0.01202 0.00531 -0.1769 0.8717 0.3939
-1.250 0.5519 0.01189 0.00522 -0.1774 0.8644 0.4256
-1.000 0.5882 0.01166 0.00505 -0.1790 0.8587 0.4584
-0.750 0.6252 0.01146 0.00489 -0.1808 0.8526 0.4902
-0.500 0.6593 0.01132 0.00480 -0.1820 0.8445 0.5197
-0.250 0.6966 0.01117 0.00469 -0.1838 0.8370 0.5496
0.000 0.7324 0.01105 0.00461 -0.1853 0.8281 0.5784
0.250 0.7654 0.01097 0.00457 -0.1862 0.8178 0.6061
0.500 0.8007 0.01089 0.00451 -0.1875 0.8074 0.6343
0.750 0.8342 0.01083 0.00448 -0.1885 0.7956 0.6613
1.000 0.8644 0.01083 0.00450 -0.1888 0.7821 0.6872
1.250 0.8943 0.01084 0.00454 -0.1889 0.7678 0.7135
1.500 0.9228 0.01088 0.00458 -0.1888 0.7527 0.7388
1.750 0.9503 0.01094 0.00464 -0.1885 0.7367 0.7644
2.000 0.9765 0.01103 0.00471 -0.1879 0.7201 0.7908
2.250 1.0008 0.01113 0.00481 -0.1869 0.7031 0.8177
2.500 1.0229 0.01123 0.00490 -0.1854 0.6856 0.8466
2.750 1.0430 0.01132 0.00498 -0.1835 0.6678 0.8802
3.250 1.0842 0.01153 0.00511 -0.1801 0.6300 1.0000
3.500 1.1098 0.01182 0.00530 -0.1796 0.6095 1.0000
3.750 1.1344 0.01212 0.00552 -0.1790 0.5882 1.0000
4.000 1.1585 0.01245 0.00577 -0.1782 0.5671 1.0000
4.250 1.1818 0.01280 0.00604 -0.1773 0.5461 1.0000
4.500 1.2046 0.01316 0.00633 -0.1763 0.5241 1.0000
4.750 1.2264 0.01357 0.00665 -0.1752 0.5017 1.0000
5.000 1.2478 0.01398 0.00699 -0.1739 0.4781 1.0000
5.500 1.2885 0.01489 0.00775 -0.1711 0.4314 1.0000
5.750 1.3077 0.01539 0.00818 -0.1695 0.4086 1.0000
6.000 1.3265 0.01589 0.00862 -0.1679 0.3851 1.0000
6.500 1.3614 0.01701 0.00961 -0.1642 0.3378 1.0000
6.750 1.3777 0.01765 0.01018 -0.1621 0.3134 1.0000
7.000 1.3938 0.01832 0.01077 -0.1601 0.2885 1.0000
7.250 1.4095 0.01903 0.01141 -0.1581 0.2644 1.0000
7.500 1.4239 0.01984 0.01212 -0.1559 0.2392 1.0000
7.750 1.4381 0.02068 0.01288 -0.1538 0.2133 1.0000
8.000 1.4512 0.02160 0.01370 -0.1515 0.1867 1.0000
8.250 1.4636 0.02261 0.01459 -0.1492 0.1608 1.0000
8.500 1.4754 0.02368 0.01554 -0.1469 0.1374 1.0000
8.750 1.4874 0.02476 0.01654 -0.1446 0.1159 1.0000
9.000 1.4986 0.02590 0.01762 -0.1423 0.0977 1.0000
9.250 1.5102 0.02704 0.01873 -0.1401 0.0822 1.0000
9.500 1.5215 0.02820 0.01988 -0.1380 0.0697 1.0000
9.750 1.5318 0.02946 0.02114 -0.1357 0.0577 1.0000
10.000 1.5406 0.03086 0.02253 -0.1334 0.0461 1.0000
10.250 1.5477 0.03244 0.02408 -0.1310 0.0356 1.0000
10.500 1.5537 0.03415 0.02581 -0.1285 0.0275 1.0000
10.750 1.5599 0.03587 0.02759 -0.1262 0.0223 1.0000
11.000 1.5662 0.03762 0.02945 -0.1239 0.0195 1.0000
11.250 1.5712 0.03954 0.03146 -0.1218 0.0178 1.0000
11.500 1.5753 0.04159 0.03362 -0.1197 0.0166 1.0000
11.750 1.5795 0.04368 0.03588 -0.1177 0.0157 1.0000
12.000 1.5825 0.04595 0.03829 -0.1159 0.0151 1.0000
12.250 1.5843 0.04842 0.04092 -0.1142 0.0145 1.0000
12.500 1.5842 0.05118 0.04382 -0.1127 0.0140 1.0000
12.750 1.5816 0.05432 0.04709 -0.1113 0.0136 1.0000
13.000 1.5804 0.05744 0.05037 -0.1101 0.0132 1.0000
13.250 1.5790 0.06071 0.05382 -0.1093 0.0129 1.0000
13.500 1.5772 0.06417 0.05744 -0.1087 0.0125 1.0000
13.750 1.5743 0.06788 0.06132 -0.1083 0.0121 1.0000
14.000 1.5709 0.07181 0.06540 -0.1082 0.0118 1.0000
14.250 1.5670 0.07596 0.06971 -0.1084 0.0116 1.0000
14.500 1.5619 0.08040 0.07431 -0.1089 0.0114 1.0000
14.750 1.5564 0.08504 0.07910 -0.1096 0.0112 1.0000
15.000 1.5508 0.08983 0.08406 -0.1105 0.0111 1.0000
15.250 1.5446 0.09482 0.08919 -0.1118 0.0109 1.0000
15.500 1.5386 0.09989 0.09440 -0.1132 0.0108 1.0000
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Polar data table (+)
Polar graphs
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