E216 (10.4%) (e216-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: E216 (10.4%) (e216-il) Reynolds number: 200,000 Max Cl/Cd: 99.18 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e216-il-200000.txt Download as CSV file: xf-e216-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3733 0.10910 0.10592 -0.0237 1.0000 0.0451
-7.750 -0.3772 0.10705 0.10392 -0.0226 1.0000 0.0461
-7.500 -0.3785 0.10464 0.10154 -0.0227 0.9993 0.0474
-7.250 -0.3644 0.10058 0.09748 -0.0287 0.9952 0.0496
-7.000 -0.3649 0.09658 0.09352 -0.0391 0.9866 0.0517
-6.750 -0.3556 0.08958 0.08655 -0.0508 0.9780 0.0523
-6.500 -0.3404 0.08679 0.08375 -0.0467 0.9764 0.0536
-6.250 -0.3247 0.08417 0.08113 -0.0474 0.9712 0.0551
-6.000 -0.3045 0.08038 0.07734 -0.0521 0.9660 0.0573
-5.750 -0.2868 0.07527 0.07222 -0.0599 0.9582 0.0606
-5.500 -0.2423 0.06176 0.05858 -0.0869 0.9526 0.0659
-5.250 -0.1723 0.03846 0.03398 -0.1194 0.9503 0.0434
-5.000 -0.1249 0.03297 0.02791 -0.1267 0.9486 0.0386
-4.750 -0.0583 0.02677 0.02038 -0.1366 0.9512 0.0341
-4.500 -0.0218 0.02485 0.01810 -0.1388 0.9471 0.0340
-4.250 0.0185 0.02323 0.01632 -0.1417 0.9446 0.0351
-4.000 0.0602 0.02209 0.01509 -0.1446 0.9425 0.0371
-3.750 0.1033 0.02130 0.01417 -0.1477 0.9408 0.0414
-3.250 0.1832 0.01916 0.01215 -0.1533 0.9333 0.0816
-3.000 0.2260 0.01844 0.01172 -0.1568 0.9305 0.1614
-2.750 0.2685 0.01803 0.01153 -0.1601 0.9281 0.2347
-2.500 0.3060 0.01775 0.01134 -0.1622 0.9242 0.2903
-2.000 0.3800 0.01720 0.01095 -0.1659 0.9151 0.3857
-1.750 0.4227 0.01685 0.01068 -0.1687 0.9131 0.4334
-1.500 0.4499 0.01673 0.01065 -0.1685 0.9048 0.4696
-1.250 0.4899 0.01639 0.01035 -0.1707 0.9015 0.5114
-1.000 0.5321 0.01595 0.01001 -0.1732 0.8994 0.5511
-0.750 0.5605 0.01580 0.00993 -0.1731 0.8915 0.5851
-0.500 0.5993 0.01537 0.00957 -0.1748 0.8879 0.6219
-0.250 0.6408 0.01482 0.00910 -0.1770 0.8857 0.6573
0.000 0.6813 0.01431 0.00867 -0.1790 0.8829 0.6921
0.250 0.7085 0.01409 0.00853 -0.1784 0.8741 0.7231
0.500 0.7505 0.01353 0.00804 -0.1806 0.8712 0.7573
0.750 0.7803 0.01324 0.00783 -0.1804 0.8633 0.7888
1.000 0.8180 0.01278 0.00743 -0.1817 0.8577 0.8220
1.250 0.8475 0.01243 0.00715 -0.1814 0.8493 0.8550
1.500 0.8784 0.01197 0.00672 -0.1812 0.8415 0.8930
1.750 0.8955 0.01152 0.00634 -0.1783 0.8293 0.9860
2.000 0.9371 0.01138 0.00614 -0.1811 0.8185 1.0000
2.250 0.9775 0.01127 0.00596 -0.1836 0.8070 1.0000
2.500 1.0146 0.01122 0.00586 -0.1853 0.7938 1.0000
2.750 1.0476 0.01125 0.00583 -0.1862 0.7787 1.0000
3.000 1.0779 0.01134 0.00586 -0.1865 0.7620 1.0000
3.250 1.1069 0.01145 0.00594 -0.1866 0.7441 1.0000
3.500 1.1354 0.01160 0.00602 -0.1865 0.7253 1.0000
3.750 1.1639 0.01177 0.00611 -0.1865 0.7062 1.0000
4.000 1.1901 0.01200 0.00627 -0.1860 0.6861 1.0000
4.250 1.2148 0.01225 0.00648 -0.1852 0.6650 1.0000
4.500 1.2400 0.01253 0.00667 -0.1845 0.6438 1.0000
4.750 1.2625 0.01284 0.00693 -0.1833 0.6208 1.0000
5.000 1.2853 0.01319 0.00720 -0.1821 0.5979 1.0000
5.250 1.3064 0.01355 0.00751 -0.1807 0.5739 1.0000
5.500 1.3275 0.01396 0.00784 -0.1792 0.5502 1.0000
5.750 1.3473 0.01438 0.00820 -0.1776 0.5254 1.0000
6.000 1.3664 0.01484 0.00861 -0.1758 0.5005 1.0000
6.250 1.3846 0.01535 0.00903 -0.1739 0.4751 1.0000
6.500 1.4018 0.01586 0.00949 -0.1718 0.4485 1.0000
6.750 1.4180 0.01643 0.00999 -0.1696 0.4217 1.0000
7.000 1.4325 0.01704 0.01052 -0.1671 0.3954 1.0000
7.250 1.4461 0.01769 0.01110 -0.1645 0.3694 1.0000
7.500 1.4594 0.01837 0.01172 -0.1618 0.3424 1.0000
7.750 1.4716 0.01914 0.01240 -0.1591 0.3144 1.0000
8.000 1.4823 0.02000 0.01315 -0.1561 0.2846 1.0000
8.250 1.4925 0.02094 0.01398 -0.1533 0.2545 1.0000
8.500 1.5023 0.02196 0.01489 -0.1504 0.2250 1.0000
8.750 1.5119 0.02306 0.01586 -0.1477 0.1965 1.0000
9.000 1.5212 0.02423 0.01692 -0.1449 0.1708 1.0000
9.250 1.5305 0.02545 0.01806 -0.1423 0.1488 1.0000
9.500 1.5401 0.02669 0.01926 -0.1398 0.1282 1.0000
9.750 1.5478 0.02811 0.02061 -0.1371 0.1085 1.0000
10.000 1.5548 0.02963 0.02207 -0.1345 0.0881 1.0000
10.250 1.5575 0.03157 0.02390 -0.1315 0.0666 1.0000
10.500 1.5536 0.03416 0.02634 -0.1278 0.0481 1.0000
10.750 1.5509 0.03673 0.02893 -0.1244 0.0392 1.0000
11.000 1.5514 0.03908 0.03140 -0.1215 0.0348 1.0000
11.250 1.5516 0.04152 0.03393 -0.1190 0.0321 1.0000
11.500 1.5445 0.04482 0.03727 -0.1162 0.0304 1.0000
11.750 1.5481 0.04719 0.03983 -0.1143 0.0291 1.0000
12.000 1.5505 0.04975 0.04254 -0.1125 0.0277 1.0000
12.250 1.5528 0.05238 0.04528 -0.1110 0.0264 1.0000
12.500 1.5540 0.05520 0.04817 -0.1096 0.0253 1.0000
12.750 1.5535 0.05846 0.05149 -0.1082 0.0243 1.0000
13.000 1.5569 0.06157 0.05471 -0.1068 0.0235 1.0000
13.250 1.5622 0.06435 0.05767 -0.1057 0.0230 1.0000
13.500 1.5673 0.06726 0.06076 -0.1047 0.0225 1.0000
13.750 1.5725 0.07028 0.06397 -0.1038 0.0221 1.0000
14.000 1.5764 0.07355 0.06743 -0.1030 0.0217 1.0000
14.250 1.5787 0.07702 0.07113 -0.1024 0.0213 1.0000
14.500 1.5791 0.08081 0.07514 -0.1019 0.0210 1.0000
14.750 1.5774 0.08494 0.07950 -0.1017 0.0209 1.0000
15.000 1.5729 0.08948 0.08429 -0.1019 0.0208 1.0000
15.250 1.5662 0.09430 0.08936 -0.1024 0.0206 1.0000
15.500 1.5568 0.09966 0.09498 -0.1035 0.0205 1.0000
15.750 1.5479 0.10493 0.10046 -0.1050 0.0203 1.0000
16.000 1.5363 0.11084 0.10661 -0.1072 0.0202 1.0000
16.250 1.5193 0.11801 0.11407 -0.1104 0.0203 1.0000
16.500 1.5025 0.12538 0.12169 -0.1142 0.0203 1.0000
16.750 1.4945 0.13106 0.12751 -0.1174 0.0199 1.0000
17.000 1.4613 0.14297 0.13981 -0.1253 0.0205 1.0000
17.250 1.4294 0.15562 0.15279 -0.1343 0.0212 1.0000
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Polar data table (+)
Polar graphs
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