E205 (10.48%) (e205-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: E205 (10.48%) (e205-il) Reynolds number: 50,000 Max Cl/Cd: 32.6 at α=9.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e205-il-50000.txt Download as CSV file: xf-e205-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: E205 (10.48%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3786 0.10487 0.09821 -0.0148 1.0000 0.2378
-8.500 -0.3818 0.10225 0.09567 -0.0156 1.0000 0.2462
-8.250 -0.3868 0.10049 0.09400 -0.0161 1.0000 0.2574
-8.000 -0.3723 0.09640 0.08994 -0.0152 1.0000 0.2701
-7.750 -0.3648 0.09296 0.08656 -0.0146 1.0000 0.2814
-7.500 -0.3650 0.09020 0.08390 -0.0144 1.0000 0.2924
-7.250 -0.3692 0.08776 0.08158 -0.0139 1.0000 0.3053
-7.000 -0.3806 0.08603 0.08000 -0.0129 1.0000 0.3184
-6.750 -0.3860 0.08380 0.07792 -0.0113 1.0000 0.3328
-6.500 -0.3786 0.08056 0.07475 -0.0095 1.0000 0.3485
-6.000 -0.3659 0.07461 0.06897 -0.0053 1.0000 0.3819
-5.750 -0.3665 0.07227 0.06675 -0.0026 1.0000 0.4015
-5.000 -0.4222 0.05333 0.04720 -0.0292 1.0000 0.1640
-4.750 -0.4162 0.04802 0.04122 -0.0304 1.0000 0.1383
-4.500 -0.4069 0.04401 0.03643 -0.0301 1.0000 0.1260
-4.250 -0.3957 0.04134 0.03363 -0.0289 1.0000 0.1235
-4.000 -0.3822 0.03879 0.03071 -0.0280 1.0000 0.1214
-3.750 -0.3665 0.03664 0.02812 -0.0272 1.0000 0.1218
-3.500 -0.3486 0.03476 0.02575 -0.0264 1.0000 0.1238
-3.250 -0.3292 0.03309 0.02356 -0.0256 1.0000 0.1258
-3.000 -0.3098 0.03139 0.02160 -0.0248 1.0000 0.1289
-2.750 -0.2669 0.02983 0.01965 -0.0278 0.9912 0.1396
-2.500 -0.2213 0.02838 0.01817 -0.0313 0.9810 0.1668
-2.250 -0.1749 0.02675 0.01691 -0.0347 0.9714 0.2499
-2.000 -0.0936 0.02234 0.01558 -0.0411 0.9684 1.0000
-1.750 -0.0457 0.02293 0.01533 -0.0460 0.9557 1.0000
-1.500 -0.0011 0.02348 0.01531 -0.0501 0.9431 1.0000
-1.250 0.0359 0.02400 0.01542 -0.0528 0.9304 1.0000
-1.000 0.0713 0.02454 0.01561 -0.0552 0.9180 1.0000
-0.750 0.1058 0.02510 0.01585 -0.0573 0.9065 1.0000
-0.500 0.1438 0.02566 0.01614 -0.0599 0.8956 1.0000
-0.250 0.1842 0.02619 0.01643 -0.0629 0.8851 1.0000
0.000 0.2074 0.02684 0.01689 -0.0629 0.8735 1.0000
0.250 0.2347 0.02750 0.01739 -0.0636 0.8627 1.0000
0.500 0.2760 0.02804 0.01777 -0.0665 0.8536 1.0000
0.750 0.2970 0.02880 0.01840 -0.0661 0.8428 1.0000
1.000 0.3165 0.02963 0.01913 -0.0655 0.8324 1.0000
1.250 0.3543 0.03024 0.01964 -0.0677 0.8238 1.0000
1.500 0.3716 0.03114 0.02047 -0.0667 0.8135 1.0000
1.750 0.3861 0.03217 0.02143 -0.0655 0.8039 1.0000
2.000 0.4309 0.03266 0.02189 -0.0684 0.7958 1.0000
2.250 0.4307 0.03403 0.02320 -0.0652 0.7853 1.0000
2.500 0.4491 0.03510 0.02425 -0.0646 0.7763 1.0000
2.750 0.4810 0.03590 0.02506 -0.0656 0.7676 1.0000
3.000 0.4820 0.03742 0.02654 -0.0629 0.7580 1.0000
3.250 0.5106 0.03836 0.02750 -0.0635 0.7492 1.0000
3.500 0.5227 0.03971 0.02884 -0.0622 0.7400 1.0000
3.750 0.5320 0.04117 0.03033 -0.0607 0.7305 1.0000
4.000 0.5725 0.04189 0.03112 -0.0624 0.7217 1.0000
4.250 0.5672 0.04379 0.03302 -0.0595 0.7115 1.0000
4.500 0.5803 0.04529 0.03456 -0.0585 0.7017 1.0000
4.750 0.6144 0.04618 0.03554 -0.0593 0.6916 1.0000
5.000 0.6203 0.04791 0.03733 -0.0577 0.6807 1.0000
5.250 0.6275 0.04966 0.03913 -0.0562 0.6694 1.0000
5.500 0.6450 0.05111 0.04067 -0.0555 0.6579 1.0000
5.750 0.6688 0.05231 0.04198 -0.0552 0.6455 1.0000
6.000 0.6948 0.05337 0.04320 -0.0549 0.6323 1.0000
6.250 0.7190 0.05442 0.04438 -0.0542 0.6183 1.0000
6.500 0.7393 0.05559 0.04569 -0.0533 0.6037 1.0000
6.750 0.7529 0.05705 0.04727 -0.0519 0.5884 1.0000
7.000 0.7636 0.05867 0.04900 -0.0505 0.5725 1.0000
7.250 0.7742 0.06028 0.05076 -0.0489 0.5556 1.0000
7.500 0.7937 0.06125 0.05190 -0.0475 0.5374 1.0000
7.750 0.8556 0.05871 0.04975 -0.0460 0.5178 1.0000
8.000 0.8578 0.06067 0.05181 -0.0440 0.4987 1.0000
8.250 0.9929 0.04906 0.04099 -0.0406 0.4728 1.0000
8.500 1.0547 0.04365 0.03594 -0.0374 0.4433 1.0000
8.750 1.0932 0.04029 0.03277 -0.0339 0.4079 1.0000
9.000 1.1413 0.03565 0.02797 -0.0306 0.3584 1.0000
9.250 1.1523 0.03535 0.02748 -0.0266 0.3133 1.0000
9.500 1.1589 0.03606 0.02786 -0.0227 0.2703 1.0000
9.750 1.1653 0.03758 0.02892 -0.0194 0.2312 1.0000
10.000 1.1676 0.03990 0.03108 -0.0163 0.1995 1.0000
10.250 1.1701 0.04235 0.03333 -0.0134 0.1711 1.0000
10.500 1.1727 0.04484 0.03558 -0.0109 0.1464 1.0000
10.750 1.1715 0.04746 0.03823 -0.0081 0.1282 1.0000
11.000 1.1787 0.05038 0.04108 -0.0061 0.1117 1.0000
11.500 1.1926 0.05731 0.04833 -0.0029 0.0937 1.0000
11.750 1.1854 0.06083 0.05225 -0.0006 0.0911 1.0000
12.000 1.1780 0.06463 0.05636 0.0011 0.0891 1.0000
12.250 1.1698 0.06860 0.06058 0.0023 0.0872 1.0000
12.500 1.1843 0.07329 0.06521 0.0026 0.0831 1.0000
12.750 1.1642 0.07749 0.06968 0.0032 0.0830 1.0000
13.000 1.1471 0.08235 0.07476 0.0031 0.0833 1.0000
13.250 1.0638 0.09150 0.08452 -0.0029 0.0912 1.0000
13.500 1.0353 0.09926 0.09238 -0.0069 0.0930 1.0000
13.750 1.0095 0.10765 0.10084 -0.0112 0.0945 1.0000
14.000 0.9897 0.11599 0.10921 -0.0153 0.0956 1.0000
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Polar data table (+)
Polar graphs
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