E231 (e231-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: E231 (e231-il) Reynolds number: 50,000 Max Cl/Cd: 30.46 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e231-il-50000-n5.txt Download as CSV file: xf-e231-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E231
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.2879 0.11580 0.10940 -0.0464 1.0000 0.0488
-11.000 -0.3684 0.11696 0.10994 -0.0465 1.0000 0.0488
-10.750 -0.3680 0.11325 0.10630 -0.0475 1.0000 0.0462
-10.250 -0.3833 0.10411 0.09736 -0.0523 1.0000 0.0401
-10.000 -0.3847 0.10112 0.09444 -0.0518 1.0000 0.0393
-9.750 -0.3902 0.09820 0.09162 -0.0514 1.0000 0.0387
-9.500 -0.4005 0.09507 0.08860 -0.0509 1.0000 0.0381
-9.250 -0.4128 0.09237 0.08600 -0.0501 1.0000 0.0376
-9.000 -0.4296 0.08940 0.08313 -0.0494 1.0000 0.0372
-8.750 -0.4485 0.08661 0.08042 -0.0486 1.0000 0.0367
-8.500 -0.4704 0.08423 0.07811 -0.0468 1.0000 0.0362
-8.250 -0.4954 0.08219 0.07613 -0.0438 1.0000 0.0359
-8.000 -0.5195 0.08035 0.07432 -0.0401 1.0000 0.0355
-7.750 -0.5398 0.07784 0.07179 -0.0371 1.0000 0.0351
-7.500 -0.5581 0.07503 0.06894 -0.0342 1.0000 0.0347
-7.250 -0.5587 0.07003 0.06371 -0.0356 0.9937 0.0339
-7.000 -0.5584 0.06535 0.05873 -0.0361 0.9874 0.0331
-6.750 -0.5542 0.06076 0.05374 -0.0361 0.9820 0.0323
-6.500 -0.5493 0.05669 0.04923 -0.0351 0.9762 0.0318
-6.250 -0.5375 0.05282 0.04478 -0.0345 0.9714 0.0312
-6.000 -0.5261 0.04967 0.04123 -0.0332 0.9666 0.0313
-5.750 -0.5111 0.04668 0.03780 -0.0321 0.9619 0.0315
-5.500 -0.4907 0.04426 0.03509 -0.0321 0.9581 0.0331
-5.250 -0.4719 0.04222 0.03264 -0.0312 0.9539 0.0346
-5.000 -0.4516 0.04007 0.03005 -0.0301 0.9495 0.0367
-4.750 -0.4252 0.03804 0.02752 -0.0299 0.9458 0.0386
-4.500 -0.3936 0.03610 0.02507 -0.0301 0.9430 0.0404
-4.250 -0.3703 0.03432 0.02317 -0.0293 0.9392 0.0433
-4.000 -0.3438 0.03318 0.02185 -0.0290 0.9351 0.0497
-3.750 -0.3129 0.03194 0.02042 -0.0293 0.9320 0.0566
-3.500 -0.2804 0.03084 0.01920 -0.0302 0.9292 0.0727
-3.250 -0.2593 0.02984 0.01819 -0.0291 0.9244 0.0955
-3.000 -0.2384 0.02819 0.01720 -0.0284 0.9201 0.1830
-2.750 -0.1858 0.02669 0.01872 -0.0285 0.9217 0.8624
-2.500 -0.0031 0.02806 0.01885 -0.0552 0.9328 0.9860
-2.250 0.0562 0.02790 0.01822 -0.0624 0.9312 1.0000
-2.000 0.0765 0.02796 0.01803 -0.0622 0.9250 1.0000
-1.750 0.0972 0.02804 0.01790 -0.0618 0.9186 1.0000
-1.500 0.1252 0.02815 0.01777 -0.0628 0.9137 1.0000
-1.250 0.1385 0.02831 0.01778 -0.0610 0.9059 1.0000
-1.000 0.1689 0.02846 0.01774 -0.0623 0.9011 1.0000
-0.750 0.1797 0.02868 0.01784 -0.0600 0.8928 1.0000
-0.500 0.2093 0.02886 0.01788 -0.0610 0.8875 1.0000
-0.250 0.2207 0.02912 0.01802 -0.0587 0.8790 1.0000
0.000 0.2506 0.02931 0.01810 -0.0597 0.8735 1.0000
0.250 0.2616 0.02959 0.01832 -0.0572 0.8645 1.0000
0.500 0.2937 0.02978 0.01841 -0.0585 0.8590 1.0000
0.750 0.3029 0.03009 0.01867 -0.0556 0.8492 1.0000
1.000 0.3386 0.03024 0.01877 -0.0574 0.8441 1.0000
1.250 0.3461 0.03057 0.01907 -0.0542 0.8334 1.0000
1.500 0.3645 0.03083 0.01930 -0.0529 0.8247 1.0000
1.750 0.3921 0.03099 0.01946 -0.0531 0.8173 1.0000
2.000 0.4036 0.03129 0.01975 -0.0505 0.8068 1.0000
2.250 0.4427 0.03130 0.01977 -0.0525 0.8011 1.0000
2.500 0.4507 0.03160 0.02008 -0.0493 0.7893 1.0000
2.750 0.4634 0.03184 0.02036 -0.0468 0.7780 1.0000
3.000 0.4844 0.03196 0.02051 -0.0456 0.7682 1.0000
3.250 0.5155 0.03188 0.02050 -0.0459 0.7599 1.0000
3.500 0.5274 0.03207 0.02072 -0.0432 0.7475 1.0000
3.750 0.5419 0.03219 0.02090 -0.0408 0.7353 1.0000
4.000 0.5591 0.03224 0.02105 -0.0388 0.7234 1.0000
4.250 0.5798 0.03218 0.02107 -0.0373 0.7118 1.0000
4.500 0.6155 0.03167 0.02069 -0.0377 0.7030 1.0000
4.750 0.6313 0.03160 0.02070 -0.0353 0.6896 1.0000
5.000 0.6486 0.03145 0.02068 -0.0330 0.6760 1.0000
5.250 0.6673 0.03121 0.02056 -0.0308 0.6622 1.0000
5.500 0.6876 0.03090 0.02037 -0.0288 0.6479 1.0000
5.750 0.7099 0.03049 0.02009 -0.0270 0.6332 1.0000
6.000 0.7227 0.03042 0.02017 -0.0241 0.6154 1.0000
6.250 0.7403 0.03020 0.02007 -0.0217 0.5972 1.0000
6.500 0.7656 0.02965 0.01966 -0.0201 0.5787 1.0000
6.750 0.7859 0.02937 0.01951 -0.0180 0.5572 1.0000
7.000 0.8149 0.02877 0.01904 -0.0169 0.5338 1.0000
7.250 0.8363 0.02859 0.01891 -0.0150 0.5064 1.0000
7.500 0.8583 0.02848 0.01880 -0.0132 0.4763 1.0000
7.750 0.8747 0.02872 0.01901 -0.0109 0.4452 1.0000
8.000 0.8885 0.02917 0.01944 -0.0084 0.4140 1.0000
8.250 0.9001 0.02980 0.02000 -0.0058 0.3840 1.0000
8.500 0.9097 0.03060 0.02072 -0.0032 0.3552 1.0000
8.750 0.9184 0.03152 0.02158 -0.0007 0.3280 1.0000
9.000 0.9267 0.03254 0.02253 0.0017 0.3028 1.0000
9.250 0.9344 0.03365 0.02361 0.0040 0.2789 1.0000
9.500 0.9422 0.03487 0.02483 0.0061 0.2562 1.0000
9.750 0.9494 0.03614 0.02604 0.0082 0.2355 1.0000
10.000 0.9571 0.03750 0.02750 0.0100 0.2154 1.0000
10.250 0.9646 0.03893 0.02894 0.0118 0.1972 1.0000
10.500 0.9725 0.04043 0.03044 0.0135 0.1808 1.0000
10.750 0.9801 0.04199 0.03201 0.0151 0.1656 1.0000
11.000 0.9871 0.04365 0.03371 0.0166 0.1513 1.0000
11.250 0.9949 0.04538 0.03551 0.0179 0.1384 1.0000
11.500 1.0006 0.04725 0.03750 0.0193 0.1262 1.0000
11.750 1.0082 0.04920 0.03962 0.0205 0.1153 1.0000
12.000 1.0145 0.05131 0.04188 0.0217 0.1055 1.0000
12.250 1.0182 0.05344 0.04406 0.0228 0.0971 1.0000
12.500 1.0216 0.05591 0.04679 0.0238 0.0891 1.0000
12.750 1.0237 0.05852 0.04954 0.0248 0.0822 1.0000
13.000 1.0224 0.06128 0.05247 0.0255 0.0760 1.0000
13.250 1.0237 0.06425 0.05558 0.0261 0.0709 1.0000
13.500 1.0187 0.06789 0.05954 0.0265 0.0666 1.0000
13.750 1.0164 0.07079 0.06244 0.0266 0.0623 1.0000
14.000 1.0082 0.07501 0.06690 0.0264 0.0594 1.0000
14.250 0.9944 0.08013 0.07236 0.0255 0.0574 1.0000
14.500 0.9799 0.08564 0.07815 0.0240 0.0561 1.0000
14.750 0.9627 0.09174 0.08446 0.0218 0.0548 1.0000
15.000 0.9417 0.09910 0.09205 0.0185 0.0549 1.0000
15.250 0.9145 0.10840 0.10156 0.0136 0.0558 1.0000
15.500 0.8819 0.11999 0.11328 0.0070 0.0574 1.0000
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Polar data table (+)
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