E216 (10.4%) (e216-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: E216 (10.4%) (e216-il) Reynolds number: 100,000 Max Cl/Cd: 68.53 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e216-il-100000-n5.txt Download as CSV file: xf-e216-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3594 0.12077 0.11599 -0.0324 1.0000 0.0547
-8.750 -0.3665 0.11847 0.11377 -0.0325 1.0000 0.0550
-8.500 -0.3710 0.11599 0.11134 -0.0320 1.0000 0.0550
-8.250 -0.3761 0.11328 0.10870 -0.0327 0.9994 0.0552
-8.000 -0.3589 0.10567 0.10102 -0.0322 0.9980 0.0343
-7.500 -0.3476 0.09473 0.09011 -0.0414 0.9892 0.0284
-7.250 -0.3368 0.09125 0.08663 -0.0444 0.9852 0.0278
-7.000 -0.3320 0.08762 0.08303 -0.0469 0.9792 0.0273
-6.750 -0.3255 0.08337 0.07879 -0.0508 0.9731 0.0268
-6.250 -0.2983 0.05325 0.04833 -0.0912 0.9555 0.0232
-6.000 -0.2610 0.04398 0.03841 -0.1064 0.9510 0.0230
-5.750 -0.2163 0.03722 0.03078 -0.1173 0.9483 0.0231
-5.500 -0.1740 0.03335 0.02631 -0.1236 0.9462 0.0236
-5.250 -0.1355 0.03150 0.02422 -0.1276 0.9439 0.0253
-5.000 -0.0933 0.02935 0.02158 -0.1318 0.9423 0.0274
-4.750 -0.0565 0.02752 0.01931 -0.1343 0.9393 0.0285
-4.500 -0.0227 0.02609 0.01773 -0.1362 0.9353 0.0298
-4.250 0.0146 0.02497 0.01649 -0.1386 0.9322 0.0321
-4.000 0.0545 0.02398 0.01530 -0.1413 0.9298 0.0361
-3.750 0.0935 0.02317 0.01439 -0.1441 0.9271 0.0440
-3.500 0.1275 0.02228 0.01351 -0.1459 0.9218 0.0581
-3.250 0.1667 0.02148 0.01289 -0.1488 0.9184 0.1035
-3.000 0.2064 0.02092 0.01252 -0.1517 0.9156 0.1699
-2.750 0.2391 0.02059 0.01226 -0.1530 0.9104 0.2158
-2.500 0.2722 0.02032 0.01205 -0.1543 0.9049 0.2618
-2.250 0.3101 0.02003 0.01180 -0.1564 0.9015 0.3110
-2.000 0.3414 0.01986 0.01169 -0.1572 0.8955 0.3529
-1.750 0.3744 0.01968 0.01153 -0.1582 0.8897 0.3941
-1.250 0.4402 0.01934 0.01128 -0.1600 0.8786 0.4727
-1.000 0.4750 0.01911 0.01108 -0.1612 0.8736 0.5102
-0.750 0.5130 0.01878 0.01079 -0.1628 0.8705 0.5482
-0.500 0.5378 0.01877 0.01083 -0.1620 0.8610 0.5800
-0.250 0.5740 0.01844 0.01053 -0.1632 0.8569 0.6161
0.000 0.6007 0.01837 0.01051 -0.1627 0.8482 0.6483
0.250 0.6347 0.01806 0.01024 -0.1634 0.8428 0.6829
0.500 0.6619 0.01792 0.01017 -0.1628 0.8343 0.7157
0.750 0.6936 0.01761 0.00991 -0.1630 0.8278 0.7504
1.000 0.7187 0.01745 0.00982 -0.1619 0.8184 0.7853
1.250 0.7494 0.01706 0.00948 -0.1618 0.8116 0.8244
1.500 0.7689 0.01688 0.00936 -0.1596 0.8005 0.8700
1.750 0.7924 0.01640 0.00893 -0.1580 0.7907 1.0000
2.000 0.8317 0.01626 0.00873 -0.1601 0.7814 1.0000
2.250 0.8653 0.01626 0.00869 -0.1612 0.7694 1.0000
2.500 0.9017 0.01622 0.00860 -0.1627 0.7576 1.0000
2.750 0.9394 0.01616 0.00853 -0.1645 0.7452 1.0000
3.000 0.9755 0.01615 0.00847 -0.1659 0.7314 1.0000
3.250 1.0094 0.01619 0.00848 -0.1669 0.7164 1.0000
3.500 1.0414 0.01629 0.00857 -0.1676 0.7000 1.0000
3.750 1.0722 0.01642 0.00868 -0.1680 0.6827 1.0000
4.000 1.1020 0.01660 0.00883 -0.1682 0.6644 1.0000
4.250 1.1313 0.01680 0.00902 -0.1683 0.6453 1.0000
4.750 1.1854 0.01734 0.00949 -0.1677 0.6040 1.0000
5.000 1.2110 0.01767 0.00980 -0.1671 0.5824 1.0000
5.250 1.2354 0.01805 0.01014 -0.1663 0.5606 1.0000
5.500 1.2584 0.01846 0.01052 -0.1653 0.5377 1.0000
5.750 1.2807 0.01891 0.01093 -0.1642 0.5146 1.0000
6.000 1.3014 0.01940 0.01141 -0.1628 0.4903 1.0000
6.250 1.3214 0.01994 0.01191 -0.1613 0.4661 1.0000
6.500 1.3402 0.02052 0.01244 -0.1596 0.4415 1.0000
6.750 1.3580 0.02113 0.01303 -0.1578 0.4168 1.0000
7.250 1.3894 0.02249 0.01435 -0.1535 0.3678 1.0000
7.500 1.4034 0.02326 0.01508 -0.1511 0.3433 1.0000
7.750 1.4166 0.02409 0.01587 -0.1487 0.3186 1.0000
8.000 1.4291 0.02498 0.01675 -0.1462 0.2939 1.0000
8.500 1.4518 0.02698 0.01869 -0.1411 0.2468 1.0000
8.750 1.4615 0.02812 0.01979 -0.1385 0.2249 1.0000
9.000 1.4718 0.02927 0.02096 -0.1360 0.2035 1.0000
9.250 1.4796 0.03061 0.02227 -0.1333 0.1826 1.0000
9.500 1.4875 0.03201 0.02365 -0.1308 0.1606 1.0000
9.750 1.4926 0.03363 0.02518 -0.1281 0.1386 1.0000
10.000 1.4982 0.03531 0.02679 -0.1256 0.1159 1.0000
10.250 1.5027 0.03714 0.02855 -0.1232 0.0971 1.0000
10.500 1.5080 0.03896 0.03039 -0.1209 0.0826 1.0000
10.750 1.5121 0.04093 0.03240 -0.1186 0.0699 1.0000
11.000 1.5148 0.04311 0.03463 -0.1164 0.0588 1.0000
11.250 1.5157 0.04553 0.03710 -0.1142 0.0498 1.0000
11.500 1.5140 0.04828 0.03990 -0.1120 0.0431 1.0000
11.750 1.5132 0.05105 0.04283 -0.1101 0.0378 1.0000
12.000 1.5083 0.05435 0.04620 -0.1083 0.0347 1.0000
12.250 1.5059 0.05751 0.04956 -0.1068 0.0320 1.0000
12.500 1.5023 0.06090 0.05312 -0.1056 0.0297 1.0000
12.750 1.4970 0.06464 0.05698 -0.1048 0.0282 1.0000
13.000 1.4914 0.06857 0.06106 -0.1042 0.0268 1.0000
13.250 1.4882 0.07238 0.06509 -0.1038 0.0255 1.0000
13.500 1.4842 0.07641 0.06933 -0.1037 0.0243 1.0000
13.750 1.4794 0.08068 0.07376 -0.1040 0.0234 1.0000
14.000 1.4742 0.08512 0.07836 -0.1045 0.0228 1.0000
14.250 1.4688 0.08971 0.08309 -0.1052 0.0222 1.0000
14.500 1.4631 0.09442 0.08792 -0.1061 0.0218 1.0000
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Polar data table (+)
Polar graphs
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