E205 (10.48%) (e205-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: E205 (10.48%) (e205-il) Reynolds number: 100,000 Max Cl/Cd: 54.9 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e205-il-100000-n5.txt Download as CSV file: xf-e205-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4072 0.09010 0.08523 -0.0297 1.0000 0.0327
-8.750 -0.4089 0.08598 0.08118 -0.0318 1.0000 0.0329
-8.500 -0.4122 0.08176 0.07703 -0.0340 1.0000 0.0328
-8.250 -0.4173 0.07760 0.07295 -0.0362 1.0000 0.0326
-8.000 -0.4263 0.07331 0.06875 -0.0385 1.0000 0.0322
-7.750 -0.4332 0.06837 0.06385 -0.0415 1.0000 0.0313
-7.500 -0.4400 0.06301 0.05848 -0.0440 1.0000 0.0311
-7.250 -0.4471 0.05762 0.05300 -0.0453 1.0000 0.0305
-7.000 -0.4538 0.05227 0.04749 -0.0454 1.0000 0.0297
-6.750 -0.4598 0.04712 0.04207 -0.0444 1.0000 0.0290
-6.500 -0.4557 0.04114 0.03553 -0.0447 0.9949 0.0282
-6.250 -0.4285 0.03576 0.02943 -0.0478 0.9819 0.0278
-6.000 -0.3988 0.03206 0.02517 -0.0499 0.9690 0.0279
-5.750 -0.3675 0.02915 0.02177 -0.0516 0.9561 0.0282
-5.500 -0.3363 0.02681 0.01900 -0.0528 0.9417 0.0287
-5.250 -0.3044 0.02484 0.01668 -0.0539 0.9267 0.0295
-5.000 -0.2716 0.02328 0.01484 -0.0549 0.9117 0.0310
-4.750 -0.2387 0.02204 0.01332 -0.0558 0.8960 0.0337
-4.500 -0.2066 0.02084 0.01185 -0.0564 0.8799 0.0354
-4.250 -0.1775 0.01951 0.01039 -0.0565 0.8633 0.0370
-4.000 -0.1495 0.01861 0.00938 -0.0564 0.8465 0.0393
-3.750 -0.1224 0.01786 0.00847 -0.0559 0.8300 0.0429
-3.500 -0.0963 0.01717 0.00761 -0.0553 0.8144 0.0485
-3.250 -0.0709 0.01648 0.00690 -0.0546 0.7993 0.0641
-3.000 -0.0460 0.01579 0.00635 -0.0540 0.7851 0.1108
-2.750 -0.0214 0.01517 0.00602 -0.0535 0.7717 0.1886
-2.500 0.0025 0.01453 0.00579 -0.0530 0.7588 0.2978
-2.250 0.0265 0.01396 0.00559 -0.0522 0.7469 0.4133
-2.000 0.0502 0.01340 0.00542 -0.0512 0.7359 0.5472
-1.500 0.1365 0.01258 0.00530 -0.0550 0.7151 0.8917
-1.250 0.1895 0.01266 0.00512 -0.0596 0.7046 0.9611
-1.000 0.2433 0.01267 0.00485 -0.0649 0.6949 0.9963
-0.750 0.2715 0.01273 0.00471 -0.0651 0.6853 1.0000
-0.500 0.2951 0.01282 0.00463 -0.0644 0.6760 1.0000
-0.250 0.3189 0.01293 0.00455 -0.0636 0.6682 1.0000
0.000 0.3428 0.01304 0.00455 -0.0629 0.6591 1.0000
0.250 0.3669 0.01317 0.00454 -0.0621 0.6514 1.0000
0.500 0.3910 0.01331 0.00456 -0.0615 0.6432 1.0000
0.750 0.4152 0.01345 0.00461 -0.0608 0.6358 1.0000
1.000 0.4395 0.01361 0.00467 -0.0601 0.6282 1.0000
1.250 0.4639 0.01377 0.00476 -0.0594 0.6211 1.0000
1.500 0.4884 0.01394 0.00486 -0.0588 0.6139 1.0000
1.750 0.5128 0.01413 0.00499 -0.0581 0.6069 1.0000
2.000 0.5373 0.01431 0.00514 -0.0575 0.5999 1.0000
2.250 0.5619 0.01451 0.00529 -0.0568 0.5932 1.0000
2.500 0.5863 0.01471 0.00548 -0.0562 0.5861 1.0000
2.750 0.6109 0.01492 0.00567 -0.0555 0.5798 1.0000
3.000 0.6352 0.01513 0.00591 -0.0549 0.5725 1.0000
3.250 0.6600 0.01535 0.00610 -0.0543 0.5664 1.0000
3.500 0.6841 0.01559 0.00641 -0.0536 0.5587 1.0000
3.750 0.7091 0.01580 0.00660 -0.0530 0.5527 1.0000
4.000 0.7329 0.01605 0.00693 -0.0523 0.5446 1.0000
4.250 0.7577 0.01627 0.00715 -0.0517 0.5380 1.0000
4.500 0.7815 0.01651 0.00748 -0.0509 0.5293 1.0000
4.750 0.8057 0.01673 0.00778 -0.0502 0.5211 1.0000
5.000 0.8298 0.01694 0.00804 -0.0495 0.5123 1.0000
5.250 0.8531 0.01716 0.00837 -0.0486 0.5023 1.0000
5.500 0.8769 0.01736 0.00862 -0.0478 0.4926 1.0000
5.750 0.9007 0.01753 0.00888 -0.0470 0.4824 1.0000
6.000 0.9234 0.01774 0.00922 -0.0460 0.4702 1.0000
6.250 0.9461 0.01795 0.00954 -0.0450 0.4576 1.0000
6.500 0.9685 0.01816 0.00985 -0.0440 0.4440 1.0000
6.750 0.9905 0.01836 0.01016 -0.0429 0.4290 1.0000
7.000 1.0121 0.01858 0.01050 -0.0418 0.4124 1.0000
7.250 1.0328 0.01886 0.01089 -0.0405 0.3929 1.0000
7.500 1.0525 0.01917 0.01126 -0.0391 0.3708 1.0000
7.750 1.0711 0.01957 0.01171 -0.0376 0.3439 1.0000
8.000 1.0878 0.02009 0.01222 -0.0359 0.3121 1.0000
8.250 1.1020 0.02081 0.01285 -0.0339 0.2739 1.0000
8.500 1.1135 0.02176 0.01370 -0.0317 0.2358 1.0000
8.750 1.1221 0.02293 0.01471 -0.0293 0.2007 1.0000
9.000 1.1291 0.02421 0.01586 -0.0268 0.1684 1.0000
9.250 1.1335 0.02561 0.01711 -0.0241 0.1388 1.0000
9.500 1.1357 0.02705 0.01841 -0.0212 0.1129 1.0000
9.750 1.1353 0.02854 0.01977 -0.0181 0.0914 1.0000
10.000 1.1357 0.03009 0.02125 -0.0155 0.0741 1.0000
10.250 1.1355 0.03183 0.02297 -0.0132 0.0603 1.0000
10.500 1.1349 0.03376 0.02490 -0.0112 0.0493 1.0000
10.750 1.1332 0.03597 0.02713 -0.0097 0.0401 1.0000
11.000 1.1306 0.03843 0.02966 -0.0084 0.0334 1.0000
11.250 1.1277 0.04108 0.03237 -0.0075 0.0291 1.0000
11.500 1.1228 0.04409 0.03544 -0.0068 0.0265 1.0000
11.750 1.1214 0.04687 0.03839 -0.0063 0.0246 1.0000
12.000 1.1194 0.04981 0.04147 -0.0061 0.0229 1.0000
12.250 1.1176 0.05281 0.04459 -0.0060 0.0219 1.0000
12.500 1.1153 0.05593 0.04782 -0.0060 0.0211 1.0000
12.750 1.1112 0.05934 0.05133 -0.0062 0.0203 1.0000
13.000 1.1088 0.06260 0.05467 -0.0062 0.0197 1.0000
13.250 1.1096 0.06559 0.05785 -0.0062 0.0190 1.0000
13.500 1.1099 0.06871 0.06115 -0.0064 0.0182 1.0000
13.750 1.1094 0.07203 0.06463 -0.0068 0.0175 1.0000
14.000 1.1085 0.07549 0.06824 -0.0074 0.0170 1.0000
14.250 1.1054 0.07937 0.07227 -0.0085 0.0162 1.0000
14.500 1.1018 0.08344 0.07646 -0.0098 0.0157 1.0000
14.750 1.0981 0.08763 0.08079 -0.0112 0.0154 1.0000
15.000 1.0939 0.09203 0.08536 -0.0127 0.0151 1.0000
15.250 1.0890 0.09665 0.09014 -0.0144 0.0149 1.0000
15.500 1.0825 0.10167 0.09529 -0.0163 0.0147 1.0000
15.750 1.0755 0.10702 0.10080 -0.0186 0.0145 1.0000
16.000 1.0666 0.11295 0.10690 -0.0214 0.0145 1.0000
16.250 1.0566 0.11936 0.11350 -0.0248 0.0145 1.0000
16.500 1.0439 0.12667 0.12100 -0.0288 0.0145 1.0000
16.750 1.0316 0.13417 0.12867 -0.0332 0.0145 1.0000
17.000 1.0165 0.14285 0.13755 -0.0383 0.0146 1.0000
17.250 0.9858 0.15752 0.15246 -0.0473 0.0151 1.0000
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Polar data table (+)
Polar graphs
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