E201 (11.88%) (e201-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: E201 (11.88%) (e201-il) Reynolds number: 50,000 Max Cl/Cd: 33.93 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e201-il-50000-n5.txt Download as CSV file: xf-e201-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3913 0.09798 0.09090 -0.0445 1.0000 0.0521
-9.500 -0.3935 0.09396 0.08697 -0.0458 1.0000 0.0517
-9.250 -0.3972 0.08983 0.08293 -0.0472 1.0000 0.0513
-9.000 -0.4033 0.08552 0.07873 -0.0487 1.0000 0.0508
-8.750 -0.4125 0.08098 0.07430 -0.0504 1.0000 0.0502
-8.500 -0.4263 0.07611 0.06955 -0.0524 1.0000 0.0495
-8.250 -0.4474 0.07120 0.06476 -0.0544 1.0000 0.0488
-8.000 -0.4666 0.06677 0.06036 -0.0552 1.0000 0.0481
-7.750 -0.4839 0.06273 0.05629 -0.0550 1.0000 0.0476
-7.500 -0.4984 0.05897 0.05243 -0.0541 1.0000 0.0473
-7.250 -0.5095 0.05542 0.04871 -0.0528 1.0000 0.0470
-7.000 -0.5165 0.05208 0.04513 -0.0513 1.0000 0.0468
-6.750 -0.5192 0.04891 0.04166 -0.0498 1.0000 0.0467
-6.500 -0.5061 0.04512 0.03741 -0.0508 0.9957 0.0470
-6.250 -0.4761 0.04109 0.03276 -0.0542 0.9863 0.0478
-6.000 -0.4449 0.03780 0.02887 -0.0566 0.9771 0.0490
-5.750 -0.4116 0.03508 0.02561 -0.0588 0.9685 0.0510
-5.500 -0.3779 0.03291 0.02292 -0.0605 0.9596 0.0547
-5.250 -0.3469 0.03134 0.02129 -0.0619 0.9500 0.0595
-5.000 -0.3109 0.02969 0.01930 -0.0635 0.9427 0.0648
-4.750 -0.2812 0.02826 0.01777 -0.0642 0.9327 0.0714
-4.500 -0.2497 0.02700 0.01644 -0.0653 0.9237 0.0869
-4.250 -0.2152 0.02565 0.01515 -0.0672 0.9159 0.1224
-4.000 -0.1856 0.02440 0.01426 -0.0686 0.9063 0.1907
-3.750 -0.1497 0.02321 0.01344 -0.0709 0.8999 0.2839
-3.500 -0.1240 0.02263 0.01321 -0.0708 0.8896 0.3753
-3.250 -0.0950 0.02232 0.01302 -0.0708 0.8810 0.4615
-3.000 -0.0656 0.02208 0.01284 -0.0707 0.8728 0.5282
-2.750 -0.0402 0.02195 0.01268 -0.0698 0.8635 0.5831
-2.500 -0.0100 0.02174 0.01247 -0.0695 0.8567 0.6351
-2.250 0.0127 0.02165 0.01239 -0.0679 0.8469 0.6798
-2.000 0.0432 0.02145 0.01215 -0.0675 0.8409 0.7276
-1.750 0.0648 0.02142 0.01212 -0.0656 0.8311 0.7722
-1.500 0.0979 0.02126 0.01191 -0.0656 0.8249 0.8234
-1.250 0.1357 0.02124 0.01181 -0.0670 0.8169 0.8773
-1.000 0.1969 0.02107 0.01145 -0.0731 0.8124 0.9331
-0.750 0.2569 0.02101 0.01115 -0.0799 0.8052 0.9865
-0.500 0.2898 0.02102 0.01093 -0.0817 0.7980 1.0000
-0.250 0.3065 0.02129 0.01101 -0.0805 0.7881 1.0000
0.000 0.3351 0.02138 0.01089 -0.0808 0.7817 1.0000
0.250 0.3527 0.02176 0.01114 -0.0796 0.7720 1.0000
0.500 0.3805 0.02193 0.01115 -0.0798 0.7654 1.0000
0.750 0.4010 0.02232 0.01144 -0.0789 0.7565 1.0000
1.000 0.4282 0.02255 0.01155 -0.0789 0.7501 1.0000
1.250 0.4496 0.02297 0.01189 -0.0782 0.7416 1.0000
1.500 0.4770 0.02322 0.01207 -0.0782 0.7354 1.0000
1.750 0.4978 0.02370 0.01251 -0.0774 0.7269 1.0000
2.000 0.5261 0.02394 0.01269 -0.0774 0.7210 1.0000
2.250 0.5456 0.02451 0.01325 -0.0765 0.7124 1.0000
2.500 0.5759 0.02469 0.01342 -0.0767 0.7071 1.0000
2.750 0.5930 0.02539 0.01413 -0.0755 0.6979 1.0000
3.000 0.6237 0.02556 0.01430 -0.0758 0.6927 1.0000
3.250 0.6396 0.02633 0.01512 -0.0744 0.6832 1.0000
3.500 0.6704 0.02651 0.01534 -0.0746 0.6780 1.0000
3.750 0.6859 0.02732 0.01623 -0.0732 0.6683 1.0000
4.000 0.7173 0.02746 0.01642 -0.0735 0.6631 1.0000
4.250 0.7319 0.02833 0.01737 -0.0720 0.6529 1.0000
4.500 0.7587 0.02865 0.01780 -0.0716 0.6460 1.0000
5.000 0.7991 0.02984 0.01920 -0.0696 0.6275 1.0000
5.250 0.8284 0.02994 0.01942 -0.0694 0.6200 1.0000
5.500 0.8446 0.03068 0.02032 -0.0678 0.6089 1.0000
5.750 0.8679 0.03102 0.02080 -0.0669 0.5992 1.0000
6.000 0.8976 0.03096 0.02088 -0.0665 0.5901 1.0000
6.250 0.9149 0.03149 0.02158 -0.0649 0.5776 1.0000
6.500 0.9349 0.03182 0.02211 -0.0634 0.5651 1.0000
6.750 0.9567 0.03196 0.02243 -0.0620 0.5520 1.0000
7.000 0.9789 0.03199 0.02265 -0.0606 0.5381 1.0000
7.250 1.0004 0.03197 0.02281 -0.0589 0.5229 1.0000
7.500 1.0216 0.03185 0.02292 -0.0571 0.5062 1.0000
7.750 1.0447 0.03150 0.02273 -0.0554 0.4880 1.0000
8.000 1.0557 0.03184 0.02326 -0.0526 0.4668 1.0000
8.250 1.0736 0.03164 0.02318 -0.0502 0.4435 1.0000
8.500 1.0816 0.03210 0.02379 -0.0472 0.4168 1.0000
8.750 1.0898 0.03245 0.02423 -0.0440 0.3868 1.0000
9.000 1.0941 0.03317 0.02495 -0.0407 0.3529 1.0000
9.250 1.0978 0.03409 0.02572 -0.0375 0.3150 1.0000
9.500 1.0972 0.03560 0.02704 -0.0346 0.2776 1.0000
9.750 1.0938 0.03756 0.02876 -0.0320 0.2440 1.0000
10.000 1.0893 0.03991 0.03091 -0.0298 0.2147 1.0000
10.250 1.0847 0.04250 0.03338 -0.0282 0.1886 1.0000
10.500 1.0806 0.04525 0.03604 -0.0268 0.1655 1.0000
10.750 1.0756 0.04821 0.03885 -0.0256 0.1460 1.0000
11.000 1.0716 0.05127 0.04185 -0.0248 0.1258 1.0000
11.250 1.0666 0.05454 0.04502 -0.0243 0.1082 1.0000
11.500 1.0616 0.05792 0.04830 -0.0241 0.0932 1.0000
11.750 1.0583 0.06127 0.05165 -0.0239 0.0805 1.0000
12.000 1.0565 0.06459 0.05500 -0.0237 0.0695 1.0000
12.250 1.0570 0.06774 0.05822 -0.0234 0.0614 1.0000
12.500 1.0562 0.07100 0.06143 -0.0232 0.0560 1.0000
12.750 1.0615 0.07387 0.06453 -0.0227 0.0503 1.0000
13.000 1.0629 0.07701 0.06770 -0.0228 0.0466 1.0000
13.250 1.0679 0.08003 0.07090 -0.0224 0.0433 1.0000
13.500 1.0736 0.08318 0.07434 -0.0221 0.0408 1.0000
13.750 1.0775 0.08658 0.07796 -0.0221 0.0391 1.0000
14.000 1.0795 0.09023 0.08180 -0.0225 0.0378 1.0000
14.250 1.0803 0.09410 0.08583 -0.0231 0.0368 1.0000
14.500 1.0808 0.09813 0.08998 -0.0238 0.0359 1.0000
14.750 1.0729 0.10362 0.09574 -0.0257 0.0356 1.0000
15.000 1.0604 0.11002 0.10242 -0.0286 0.0354 1.0000
15.250 1.0458 0.11717 0.10977 -0.0323 0.0353 1.0000
15.500 1.0299 0.12501 0.11783 -0.0367 0.0354 1.0000
15.750 1.0138 0.13343 0.12643 -0.0416 0.0355 1.0000
16.000 0.9976 0.14254 0.13567 -0.0471 0.0357 1.0000
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Polar data table (+)
Polar graphs
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