E195 (11.82%) (e195-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: E195 (11.82%) (e195-il) Reynolds number: 50,000 Max Cl/Cd: 31.82 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e195-il-50000-n5.txt Download as CSV file: xf-e195-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E195 (11.82%)
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 -0.3819 0.09959 0.09258 -0.0425 1.0000 0.0536
-9.500 -0.3821 0.09569 0.08876 -0.0439 1.0000 0.0532
-9.250 -0.3839 0.09168 0.08483 -0.0453 1.0000 0.0526
-9.000 -0.3869 0.08770 0.08095 -0.0467 1.0000 0.0518
-8.750 -0.3927 0.08351 0.07688 -0.0484 1.0000 0.0512
-8.500 -0.4031 0.07899 0.07248 -0.0502 1.0000 0.0505
-8.250 -0.4191 0.07438 0.06800 -0.0522 1.0000 0.0497
-8.000 -0.4377 0.06983 0.06358 -0.0535 1.0000 0.0490
-7.750 -0.4568 0.06582 0.05960 -0.0534 1.0000 0.0483
-7.500 -0.4751 0.06235 0.05611 -0.0522 1.0000 0.0478
-7.250 -0.4920 0.05924 0.05291 -0.0502 1.0000 0.0474
-7.000 -0.5028 0.05585 0.04933 -0.0489 0.9986 0.0470
-6.750 -0.4819 0.04985 0.04275 -0.0542 0.9857 0.0468
-6.500 -0.4577 0.04519 0.03747 -0.0577 0.9740 0.0470
-6.250 -0.4314 0.04139 0.03312 -0.0601 0.9629 0.0477
-6.000 -0.4021 0.03818 0.02936 -0.0622 0.9530 0.0488
-5.750 -0.3698 0.03548 0.02615 -0.0641 0.9440 0.0510
-5.500 -0.3394 0.03334 0.02343 -0.0652 0.9339 0.0547
-5.250 -0.3057 0.03145 0.02138 -0.0669 0.9262 0.0589
-5.000 -0.2733 0.02983 0.01950 -0.0679 0.9173 0.0632
-4.750 -0.2407 0.02829 0.01770 -0.0687 0.9092 0.0693
-4.500 -0.2080 0.02702 0.01634 -0.0698 0.9013 0.0826
-4.250 -0.1795 0.02584 0.01517 -0.0703 0.8919 0.1072
-4.000 -0.1460 0.02454 0.01415 -0.0722 0.8850 0.1686
-3.750 -0.1208 0.02353 0.01344 -0.0723 0.8751 0.2413
-3.500 -0.0926 0.02267 0.01295 -0.0728 0.8674 0.3335
-3.250 -0.0684 0.02220 0.01275 -0.0720 0.8583 0.4267
-3.000 -0.0444 0.02189 0.01257 -0.0710 0.8499 0.5098
-2.750 -0.0189 0.02161 0.01240 -0.0699 0.8423 0.5836
-2.500 0.0030 0.02145 0.01234 -0.0681 0.8337 0.6486
-2.250 0.0294 0.02125 0.01219 -0.0667 0.8270 0.7160
-2.000 0.0550 0.02118 0.01215 -0.0653 0.8190 0.7818
-1.750 0.0979 0.02107 0.01197 -0.0669 0.8133 0.8548
-1.500 0.1592 0.02098 0.01163 -0.0727 0.8086 0.9221
-1.250 0.2225 0.02092 0.01128 -0.0799 0.8022 0.9770
-1.000 0.2679 0.02083 0.01088 -0.0839 0.7964 1.0000
-0.750 0.2824 0.02111 0.01098 -0.0824 0.7868 1.0000
-0.500 0.3066 0.02123 0.01087 -0.0820 0.7803 1.0000
-0.250 0.3230 0.02160 0.01109 -0.0806 0.7711 1.0000
0.000 0.3477 0.02179 0.01109 -0.0802 0.7650 1.0000
0.250 0.3657 0.02220 0.01137 -0.0789 0.7564 1.0000
0.500 0.3922 0.02239 0.01141 -0.0787 0.7508 1.0000
0.750 0.4095 0.02288 0.01182 -0.0774 0.7422 1.0000
1.000 0.4372 0.02307 0.01188 -0.0773 0.7369 1.0000
1.250 0.4540 0.02364 0.01240 -0.0759 0.7282 1.0000
1.500 0.4812 0.02387 0.01255 -0.0758 0.7229 1.0000
1.750 0.4988 0.02447 0.01312 -0.0745 0.7146 1.0000
2.000 0.5251 0.02476 0.01336 -0.0743 0.7090 1.0000
2.250 0.5440 0.02535 0.01394 -0.0732 0.7013 1.0000
2.500 0.5688 0.02572 0.01430 -0.0728 0.6951 1.0000
2.750 0.5896 0.02628 0.01486 -0.0719 0.6881 1.0000
3.000 0.6121 0.02675 0.01535 -0.0712 0.6812 1.0000
3.250 0.6359 0.02721 0.01583 -0.0707 0.6750 1.0000
3.500 0.6551 0.02786 0.01654 -0.0697 0.6672 1.0000
3.750 0.6826 0.02815 0.01686 -0.0695 0.6618 1.0000
4.000 0.6979 0.02899 0.01778 -0.0681 0.6528 1.0000
4.250 0.7275 0.02917 0.01801 -0.0680 0.6477 1.0000
4.500 0.7409 0.03011 0.01909 -0.0664 0.6378 1.0000
4.750 0.7658 0.03050 0.01955 -0.0659 0.6311 1.0000
5.000 0.7847 0.03115 0.02031 -0.0647 0.6222 1.0000
5.250 0.8032 0.03181 0.02109 -0.0635 0.6132 1.0000
5.500 0.8309 0.03196 0.02139 -0.0631 0.6059 1.0000
5.750 0.8452 0.03279 0.02236 -0.0614 0.5950 1.0000
6.000 0.8710 0.03295 0.02266 -0.0607 0.5866 1.0000
6.250 0.8947 0.03314 0.02300 -0.0597 0.5767 1.0000
6.500 0.9103 0.03376 0.02378 -0.0579 0.5647 1.0000
6.750 0.9298 0.03408 0.02431 -0.0565 0.5530 1.0000
7.000 0.9536 0.03405 0.02446 -0.0552 0.5413 1.0000
7.250 0.9788 0.03382 0.02442 -0.0539 0.5288 1.0000
7.500 0.9991 0.03377 0.02456 -0.0521 0.5142 1.0000
7.750 1.0154 0.03388 0.02490 -0.0500 0.4980 1.0000
8.000 1.0317 0.03390 0.02511 -0.0477 0.4805 1.0000
8.250 1.0519 0.03352 0.02492 -0.0456 0.4614 1.0000
8.500 1.0612 0.03385 0.02541 -0.0427 0.4397 1.0000
8.750 1.0746 0.03377 0.02543 -0.0399 0.4157 1.0000
9.000 1.0816 0.03421 0.02597 -0.0369 0.3883 1.0000
9.250 1.0865 0.03494 0.02676 -0.0339 0.3567 1.0000
9.500 1.0906 0.03588 0.02762 -0.0311 0.3212 1.0000
9.750 1.0920 0.03723 0.02878 -0.0285 0.2848 1.0000
10.000 1.0895 0.03918 0.03052 -0.0262 0.2510 1.0000
10.250 1.0855 0.04152 0.03268 -0.0243 0.2216 1.0000
10.500 1.0809 0.04415 0.03516 -0.0228 0.1954 1.0000
10.750 1.0762 0.04694 0.03781 -0.0215 0.1729 1.0000
11.000 1.0713 0.04994 0.04071 -0.0206 0.1515 1.0000
11.250 1.0664 0.05304 0.04368 -0.0198 0.1333 1.0000
11.500 1.0615 0.05633 0.04691 -0.0194 0.1144 1.0000
11.750 1.0562 0.05975 0.05025 -0.0192 0.0984 1.0000
12.000 1.0517 0.06320 0.05369 -0.0192 0.0849 1.0000
12.250 1.0488 0.06662 0.05710 -0.0192 0.0735 1.0000
12.500 1.0465 0.07008 0.06059 -0.0191 0.0638 1.0000
12.750 1.0454 0.07338 0.06382 -0.0191 0.0582 1.0000
13.000 1.0482 0.07647 0.06712 -0.0188 0.0519 1.0000
13.250 1.0483 0.07974 0.07035 -0.0190 0.0480 1.0000
13.500 1.0537 0.08280 0.07370 -0.0186 0.0440 1.0000
13.750 1.0590 0.08584 0.07694 -0.0183 0.0418 1.0000
14.000 1.0629 0.08906 0.08030 -0.0184 0.0399 1.0000
14.250 1.0678 0.09213 0.08344 -0.0183 0.0383 1.0000
14.500 1.0672 0.09644 0.08801 -0.0191 0.0373 1.0000
14.750 1.0609 0.10174 0.09363 -0.0207 0.0366 1.0000
15.000 1.0506 0.10777 0.09996 -0.0232 0.0361 1.0000
15.250 1.0367 0.11478 0.10724 -0.0266 0.0357 1.0000
15.500 1.0214 0.12248 0.11517 -0.0307 0.0357 1.0000
15.750 1.0056 0.13075 0.12364 -0.0353 0.0361 1.0000
16.000 0.9871 0.14038 0.13343 -0.0410 0.0364 1.0000
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