E231 (e231-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: E231 (e231-il) Reynolds number: 200,000 Max Cl/Cd: 68.53 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e231-il-200000-n5.txt Download as CSV file: xf-e231-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.3650 0.11217 0.10864 -0.0484 1.0000 0.0216
-11.000 -0.3651 0.10814 0.10466 -0.0501 1.0000 0.0217
-10.750 -0.3639 0.10398 0.10051 -0.0487 1.0000 0.0146
-10.500 -0.3666 0.09616 0.09271 -0.0532 0.9902 0.0107
-10.250 -0.3605 0.09148 0.08805 -0.0571 0.9797 0.0105
-10.000 -0.3533 0.08678 0.08334 -0.0614 0.9712 0.0102
-9.750 -0.3479 0.08137 0.07794 -0.0666 0.9627 0.0099
-9.500 -0.3461 0.07468 0.07125 -0.0733 0.9541 0.0095
-9.250 -0.3489 0.06663 0.06317 -0.0827 0.9436 0.0094
-9.000 -0.3618 0.06013 0.05653 -0.0875 0.9317 0.0092
-8.750 -0.3762 0.05565 0.05189 -0.0878 0.9208 0.0089
-8.500 -0.3914 0.05186 0.04792 -0.0856 0.9119 0.0087
-8.250 -0.4057 0.04707 0.04284 -0.0828 0.9038 0.0083
-8.000 -0.4208 0.04018 0.03531 -0.0784 0.8967 0.0075
-7.750 -0.4201 0.03725 0.03207 -0.0756 0.8910 0.0074
-7.500 -0.4159 0.03441 0.02885 -0.0729 0.8868 0.0074
-7.250 -0.4081 0.03178 0.02585 -0.0705 0.8818 0.0073
-7.000 -0.3967 0.02936 0.02304 -0.0682 0.8774 0.0073
-6.750 -0.3819 0.02713 0.02040 -0.0662 0.8740 0.0073
-6.500 -0.3642 0.02507 0.01792 -0.0645 0.8707 0.0074
-6.250 -0.3441 0.02352 0.01610 -0.0633 0.8667 0.0074
-6.000 -0.3229 0.02179 0.01408 -0.0622 0.8634 0.0077
-5.750 -0.3006 0.02057 0.01270 -0.0613 0.8605 0.0080
-5.250 -0.2554 0.01876 0.01066 -0.0596 0.8541 0.0088
-5.000 -0.2330 0.01801 0.00981 -0.0586 0.8506 0.0098
-4.750 -0.2098 0.01746 0.00913 -0.0578 0.8476 0.0109
-4.500 -0.1872 0.01686 0.00850 -0.0570 0.8449 0.0133
-4.250 -0.1649 0.01631 0.00784 -0.0560 0.8417 0.0154
-4.000 -0.1437 0.01569 0.00717 -0.0548 0.8377 0.0184
-3.750 -0.1212 0.01516 0.00662 -0.0538 0.8344 0.0268
-3.500 -0.0994 0.01453 0.00614 -0.0527 0.8315 0.0604
-3.250 -0.0797 0.01380 0.00579 -0.0516 0.8287 0.1482
-3.000 -0.0633 0.01307 0.00559 -0.0499 0.8240 0.2740
-2.750 -0.0505 0.01217 0.00539 -0.0474 0.8202 0.4449
-2.500 -0.0382 0.01128 0.00527 -0.0442 0.8170 0.6316
-2.250 -0.0027 0.01122 0.00575 -0.0443 0.8155 0.7927
-2.000 0.0222 0.01150 0.00599 -0.0432 0.8111 0.8392
-1.750 0.0478 0.01173 0.00613 -0.0422 0.8074 0.8646
-1.500 0.0735 0.01190 0.00621 -0.0413 0.8043 0.8827
-1.250 0.1052 0.01207 0.00626 -0.0415 0.8019 0.8958
-1.000 0.1374 0.01228 0.00640 -0.0421 0.7980 0.9058
-0.750 0.1661 0.01242 0.00647 -0.0421 0.7937 0.9159
-0.500 0.2062 0.01251 0.00647 -0.0444 0.7905 0.9218
-0.250 0.2369 0.01253 0.00639 -0.0448 0.7874 0.9295
0.000 0.2775 0.01259 0.00642 -0.0475 0.7824 0.9330
0.250 0.3114 0.01258 0.00636 -0.0488 0.7775 0.9376
0.500 0.3386 0.01252 0.00623 -0.0486 0.7734 0.9431
0.750 0.3743 0.01251 0.00621 -0.0505 0.7672 0.9456
1.000 0.4083 0.01243 0.00610 -0.0518 0.7617 0.9484
1.250 0.4379 0.01238 0.00602 -0.0523 0.7557 0.9521
1.500 0.4613 0.01235 0.00598 -0.0515 0.7486 0.9568
1.750 0.4955 0.01225 0.00587 -0.0529 0.7421 0.9586
2.000 0.5273 0.01218 0.00582 -0.0539 0.7341 0.9609
2.250 0.5574 0.01212 0.00576 -0.0545 0.7258 0.9636
2.500 0.5856 0.01203 0.00566 -0.0547 0.7174 0.9665
2.750 0.6088 0.01203 0.00569 -0.0539 0.7069 0.9702
3.000 0.6404 0.01195 0.00565 -0.0549 0.6958 0.9719
3.250 0.6708 0.01189 0.00559 -0.0556 0.6831 0.9738
3.500 0.6997 0.01184 0.00555 -0.0559 0.6683 0.9760
3.750 0.7272 0.01182 0.00554 -0.0560 0.6517 0.9785
4.000 0.7528 0.01183 0.00552 -0.0557 0.6329 0.9810
4.250 0.7780 0.01189 0.00555 -0.0553 0.6096 0.9835
4.500 0.8062 0.01199 0.00556 -0.0556 0.5799 0.9853
4.750 0.8318 0.01218 0.00564 -0.0554 0.5462 0.9874
5.000 0.8553 0.01248 0.00580 -0.0549 0.5084 0.9900
5.250 0.8769 0.01289 0.00605 -0.0541 0.4679 0.9930
5.500 0.8981 0.01337 0.00636 -0.0534 0.4279 0.9955
5.750 0.9195 0.01389 0.00674 -0.0529 0.3904 0.9983
6.000 0.9366 0.01440 0.00714 -0.0514 0.3573 1.0000
6.250 0.9440 0.01487 0.00752 -0.0479 0.3306 1.0000
6.500 0.9499 0.01534 0.00790 -0.0441 0.3064 1.0000
6.750 0.9546 0.01578 0.00828 -0.0401 0.2834 1.0000
7.000 0.9569 0.01622 0.00865 -0.0356 0.2638 1.0000
7.250 0.9574 0.01662 0.00902 -0.0308 0.2452 1.0000
7.500 0.9543 0.01695 0.00933 -0.0253 0.2305 1.0000
7.750 0.9541 0.01735 0.00968 -0.0205 0.2154 1.0000
8.000 0.9578 0.01782 0.01012 -0.0165 0.1997 1.0000
8.250 0.9639 0.01839 0.01064 -0.0133 0.1827 1.0000
8.500 0.9721 0.01903 0.01123 -0.0105 0.1662 1.0000
8.750 0.9820 0.01970 0.01187 -0.0081 0.1517 1.0000
9.000 0.9928 0.02040 0.01255 -0.0060 0.1365 1.0000
9.250 1.0041 0.02114 0.01330 -0.0040 0.1233 1.0000
9.500 1.0151 0.02194 0.01410 -0.0021 0.1107 1.0000
10.000 1.0379 0.02362 0.01580 0.0014 0.0878 1.0000
10.250 1.0494 0.02451 0.01671 0.0030 0.0782 1.0000
10.500 1.0600 0.02548 0.01771 0.0047 0.0699 1.0000
10.750 1.0696 0.02656 0.01880 0.0063 0.0619 1.0000
11.000 1.0806 0.02756 0.01987 0.0077 0.0542 1.0000
11.250 1.0897 0.02872 0.02108 0.0093 0.0474 1.0000
11.500 1.0987 0.02992 0.02231 0.0107 0.0407 1.0000
11.750 1.1075 0.03117 0.02365 0.0121 0.0360 1.0000
12.000 1.1146 0.03258 0.02510 0.0135 0.0308 1.0000
12.250 1.1217 0.03403 0.02665 0.0149 0.0269 1.0000
12.500 1.1272 0.03565 0.02831 0.0162 0.0229 1.0000
12.750 1.1316 0.03740 0.03016 0.0175 0.0194 1.0000
13.000 1.1352 0.03928 0.03213 0.0186 0.0165 1.0000
13.250 1.1357 0.04147 0.03440 0.0197 0.0149 1.0000
13.500 1.1398 0.04342 0.03649 0.0206 0.0125 1.0000
13.750 1.1397 0.04584 0.03900 0.0214 0.0112 1.0000
14.000 1.1362 0.04872 0.04203 0.0220 0.0101 1.0000
14.250 1.1398 0.05097 0.04441 0.0223 0.0081 1.0000
14.500 1.1352 0.05421 0.04783 0.0225 0.0081 1.0000
14.750 1.1306 0.05762 0.05132 0.0222 0.0072 1.0000
15.000 1.1268 0.06110 0.05497 0.0219 0.0067 1.0000
15.250 1.1204 0.06508 0.05913 0.0211 0.0065 1.0000
15.500 1.1125 0.06948 0.06371 0.0200 0.0063 1.0000
15.750 1.1043 0.07415 0.06854 0.0185 0.0057 1.0000
16.000 1.0947 0.07923 0.07379 0.0167 0.0057 1.0000
16.250 1.0852 0.08450 0.07923 0.0146 0.0057 1.0000
16.500 1.0739 0.09033 0.08522 0.0119 0.0054 1.0000
16.750 1.0609 0.09666 0.09170 0.0090 0.0053 1.0000
17.000 1.0487 0.10309 0.09829 0.0058 0.0052 1.0000
17.250 1.0367 0.10962 0.10498 0.0025 0.0052 1.0000
17.500 1.0236 0.11653 0.11204 -0.0011 0.0053 1.0000
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