E201 (11.88%) (e201-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: E201 (11.88%) (e201-il) Reynolds number: 100,000 Max Cl/Cd: 57.01 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e201-il-100000-n5.txt Download as CSV file: xf-e201-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E201 (11.88%)
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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4001 0.08970 0.08470 -0.0454 1.0000 0.0295
-9.500 -0.4076 0.08466 0.07973 -0.0474 1.0000 0.0289
-9.250 -0.4205 0.07865 0.07382 -0.0501 1.0000 0.0282
-9.000 -0.4849 0.06204 0.05726 -0.0619 1.0000 0.0263
-8.750 -0.5219 0.05701 0.05210 -0.0624 1.0000 0.0258
-8.500 -0.5395 0.05367 0.04859 -0.0610 1.0000 0.0257
-8.250 -0.5525 0.05058 0.04535 -0.0590 1.0000 0.0256
-8.000 -0.5543 0.04699 0.04150 -0.0588 0.9972 0.0255
-7.750 -0.5337 0.04188 0.03580 -0.0630 0.9872 0.0255
-7.500 -0.5100 0.03769 0.03103 -0.0659 0.9773 0.0256
-7.250 -0.4833 0.03417 0.02704 -0.0683 0.9685 0.0259
-7.000 -0.4551 0.03140 0.02392 -0.0701 0.9595 0.0263
-6.750 -0.4264 0.02923 0.02146 -0.0714 0.9499 0.0269
-6.500 -0.3925 0.02757 0.01958 -0.0735 0.9429 0.0286
-6.250 -0.3629 0.02607 0.01780 -0.0744 0.9326 0.0305
-6.000 -0.3320 0.02451 0.01597 -0.0752 0.9232 0.0320
-5.750 -0.2989 0.02305 0.01428 -0.0764 0.9152 0.0331
-5.500 -0.2709 0.02170 0.01289 -0.0768 0.9043 0.0347
-5.250 -0.2407 0.02067 0.01175 -0.0775 0.8944 0.0371
-5.000 -0.2088 0.01972 0.01062 -0.0784 0.8856 0.0409
-4.750 -0.1808 0.01885 0.00970 -0.0786 0.8742 0.0484
-4.500 -0.1521 0.01796 0.00878 -0.0790 0.8637 0.0655
-4.250 -0.1227 0.01707 0.00800 -0.0795 0.8543 0.1022
-4.000 -0.0959 0.01632 0.00752 -0.0797 0.8435 0.1678
-3.750 -0.0700 0.01561 0.00716 -0.0798 0.8329 0.2530
-3.500 -0.0427 0.01511 0.00686 -0.0798 0.8236 0.3254
-3.250 -0.0162 0.01480 0.00667 -0.0795 0.8136 0.3947
-3.000 0.0101 0.01460 0.00652 -0.0791 0.8039 0.4517
-2.750 0.0378 0.01444 0.00635 -0.0788 0.7957 0.4991
-2.500 0.0637 0.01433 0.00624 -0.0782 0.7860 0.5382
-2.250 0.0904 0.01422 0.00611 -0.0777 0.7777 0.5739
-2.000 0.1169 0.01413 0.00601 -0.0772 0.7694 0.6081
-1.750 0.1430 0.01406 0.00593 -0.0766 0.7612 0.6416
-1.500 0.1694 0.01398 0.00584 -0.0760 0.7537 0.6750
-1.250 0.1947 0.01392 0.00581 -0.0751 0.7458 0.7096
-1.000 0.2207 0.01386 0.00576 -0.0743 0.7388 0.7467
-0.750 0.2458 0.01382 0.00576 -0.0734 0.7313 0.7857
-0.500 0.2733 0.01377 0.00573 -0.0727 0.7245 0.8290
-0.250 0.3054 0.01376 0.00572 -0.0731 0.7176 0.8760
0.000 0.3461 0.01376 0.00567 -0.0755 0.7108 0.9220
0.250 0.3902 0.01379 0.00560 -0.0788 0.7044 0.9623
0.500 0.4349 0.01383 0.00555 -0.0826 0.6973 0.9962
0.750 0.4610 0.01395 0.00555 -0.0825 0.6914 1.0000
1.000 0.4834 0.01412 0.00566 -0.0817 0.6840 1.0000
1.250 0.5084 0.01426 0.00570 -0.0812 0.6784 1.0000
1.500 0.5316 0.01446 0.00587 -0.0806 0.6713 1.0000
1.750 0.5568 0.01463 0.00597 -0.0801 0.6653 1.0000
2.000 0.5814 0.01483 0.00613 -0.0796 0.6590 1.0000
2.250 0.6062 0.01503 0.00632 -0.0791 0.6525 1.0000
2.500 0.6324 0.01521 0.00646 -0.0788 0.6471 1.0000
2.750 0.6563 0.01545 0.00673 -0.0782 0.6400 1.0000
3.000 0.6828 0.01564 0.00690 -0.0780 0.6344 1.0000
3.250 0.7069 0.01589 0.00720 -0.0774 0.6274 1.0000
3.500 0.7327 0.01609 0.00741 -0.0770 0.6212 1.0000
3.750 0.7575 0.01633 0.00769 -0.0765 0.6143 1.0000
4.000 0.7827 0.01654 0.00796 -0.0761 0.6070 1.0000
4.250 0.8075 0.01676 0.00823 -0.0755 0.5994 1.0000
4.500 0.8328 0.01694 0.00846 -0.0750 0.5914 1.0000
4.750 0.8566 0.01717 0.00876 -0.0743 0.5824 1.0000
5.000 0.8829 0.01729 0.00893 -0.0738 0.5742 1.0000
5.250 0.9056 0.01750 0.00926 -0.0729 0.5632 1.0000
5.500 0.9290 0.01768 0.00953 -0.0720 0.5522 1.0000
5.750 0.9529 0.01783 0.00975 -0.0712 0.5409 1.0000
6.000 0.9766 0.01796 0.00999 -0.0703 0.5289 1.0000
6.250 0.9993 0.01811 0.01023 -0.0693 0.5151 1.0000
6.500 1.0209 0.01829 0.01052 -0.0681 0.4993 1.0000
6.750 1.0418 0.01850 0.01084 -0.0668 0.4817 1.0000
7.000 1.0623 0.01871 0.01116 -0.0654 0.4619 1.0000
7.250 1.0815 0.01897 0.01150 -0.0638 0.4389 1.0000
7.500 1.0992 0.01931 0.01186 -0.0620 0.4105 1.0000
7.750 1.1146 0.01977 0.01228 -0.0598 0.3750 1.0000
8.000 1.1265 0.02045 0.01281 -0.0573 0.3316 1.0000
8.250 1.1340 0.02141 0.01357 -0.0543 0.2855 1.0000
8.500 1.1377 0.02264 0.01453 -0.0510 0.2402 1.0000
8.750 1.1381 0.02399 0.01565 -0.0473 0.2003 1.0000
9.000 1.1363 0.02547 0.01689 -0.0437 0.1624 1.0000
9.250 1.1347 0.02710 0.01828 -0.0404 0.1288 1.0000
9.500 1.1343 0.02879 0.01976 -0.0376 0.0994 1.0000
9.750 1.1358 0.03047 0.02133 -0.0353 0.0799 1.0000
10.000 1.1382 0.03221 0.02303 -0.0332 0.0626 1.0000
10.250 1.1401 0.03410 0.02491 -0.0314 0.0504 1.0000
10.750 1.1391 0.03862 0.02945 -0.0280 0.0355 1.0000
11.000 1.1403 0.04091 0.03187 -0.0267 0.0307 1.0000
11.250 1.1400 0.04340 0.03443 -0.0257 0.0281 1.0000
11.500 1.1403 0.04594 0.03706 -0.0248 0.0259 1.0000
11.750 1.1425 0.04835 0.03962 -0.0241 0.0239 1.0000
12.000 1.1437 0.05094 0.04232 -0.0235 0.0224 1.0000
12.250 1.1440 0.05369 0.04517 -0.0231 0.0215 1.0000
12.500 1.1420 0.05675 0.04832 -0.0227 0.0207 1.0000
12.750 1.1445 0.05943 0.05114 -0.0222 0.0202 1.0000
13.000 1.1474 0.06213 0.05400 -0.0218 0.0196 1.0000
13.250 1.1506 0.06486 0.05693 -0.0215 0.0191 1.0000
13.500 1.1538 0.06771 0.05994 -0.0212 0.0185 1.0000
13.750 1.1567 0.07067 0.06306 -0.0211 0.0181 1.0000
14.000 1.1588 0.07378 0.06634 -0.0211 0.0177 1.0000
14.250 1.1599 0.07714 0.06987 -0.0214 0.0174 1.0000
14.500 1.1592 0.08077 0.07368 -0.0219 0.0171 1.0000
14.750 1.1572 0.08467 0.07775 -0.0227 0.0168 1.0000
15.000 1.1537 0.08884 0.08208 -0.0239 0.0165 1.0000
15.250 1.1493 0.09328 0.08668 -0.0253 0.0163 1.0000
15.500 1.1441 0.09782 0.09131 -0.0269 0.0159 1.0000
15.750 1.1352 0.10333 0.09702 -0.0292 0.0157 1.0000
16.000 1.1241 0.10947 0.10341 -0.0321 0.0157 1.0000
16.250 1.1130 0.11585 0.11000 -0.0354 0.0157 1.0000
16.500 1.0971 0.12356 0.11796 -0.0399 0.0156 1.0000
16.750 1.0845 0.13087 0.12545 -0.0441 0.0157 1.0000
17.000 1.0697 0.13910 0.13386 -0.0493 0.0157 1.0000
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Polar data table (+)
Polar graphs
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