E205 (10.48%) (e205-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: E205 (10.48%) (e205-il) Reynolds number: 50,000 Max Cl/Cd: 34.53 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e205-il-50000-n5.txt Download as CSV file: xf-e205-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E205 (10.48%)
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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4122 0.12371 0.11661 -0.0161 1.0000 0.1101
-10.250 -0.4194 0.12136 0.11436 -0.0191 1.0000 0.1130
-10.000 -0.4216 0.11834 0.11141 -0.0215 1.0000 0.1135
-9.750 -0.4011 0.11285 0.10588 -0.0201 1.0000 0.1072
-9.500 -0.4147 0.10406 0.09712 -0.0279 1.0000 0.0589
-9.250 -0.4057 0.10050 0.09359 -0.0276 1.0000 0.0572
-9.000 -0.4026 0.09674 0.08988 -0.0287 1.0000 0.0556
-8.750 -0.4020 0.09284 0.08606 -0.0302 1.0000 0.0542
-8.500 -0.4038 0.08876 0.08207 -0.0321 1.0000 0.0528
-8.250 -0.4081 0.08453 0.07794 -0.0344 1.0000 0.0515
-8.000 -0.4174 0.07986 0.07339 -0.0374 1.0000 0.0502
-7.500 -0.4412 0.06733 0.06075 -0.0458 1.0000 0.0466
-7.250 -0.4419 0.06355 0.05692 -0.0459 1.0000 0.0463
-7.000 -0.4422 0.05985 0.05315 -0.0456 1.0000 0.0460
-6.750 -0.4420 0.05621 0.04938 -0.0450 1.0000 0.0459
-6.500 -0.4411 0.05258 0.04553 -0.0441 1.0000 0.0461
-6.250 -0.4389 0.04921 0.04185 -0.0428 1.0000 0.0464
-6.000 -0.4355 0.04614 0.03850 -0.0411 1.0000 0.0471
-5.750 -0.4302 0.04382 0.03605 -0.0393 1.0000 0.0483
-5.500 -0.4238 0.04191 0.03403 -0.0373 1.0000 0.0494
-5.250 -0.3996 0.03891 0.03061 -0.0387 0.9920 0.0506
-5.000 -0.3638 0.03552 0.02663 -0.0415 0.9791 0.0513
-4.750 -0.3274 0.03271 0.02327 -0.0439 0.9663 0.0527
-4.500 -0.2895 0.03032 0.02039 -0.0460 0.9541 0.0547
-4.250 -0.2504 0.02827 0.01789 -0.0480 0.9425 0.0577
-4.000 -0.2136 0.02674 0.01617 -0.0498 0.9299 0.0637
-3.750 -0.1760 0.02543 0.01462 -0.0515 0.9175 0.0739
-3.500 -0.1393 0.02410 0.01318 -0.0530 0.9052 0.0873
-3.000 -0.0701 0.02153 0.01123 -0.0563 0.8804 0.2231
-2.750 -0.0406 0.02036 0.01061 -0.0568 0.8679 0.3504
-2.500 -0.0155 0.01929 0.01028 -0.0558 0.8559 0.5241
-2.250 0.0235 0.01836 0.01018 -0.0555 0.8451 0.7829
-2.000 0.1375 0.01796 0.00926 -0.0705 0.8412 0.9927
-1.750 0.1697 0.01795 0.00886 -0.0716 0.8272 1.0000
-1.500 0.1940 0.01803 0.00860 -0.0711 0.8130 1.0000
-1.250 0.2176 0.01815 0.00843 -0.0704 0.7995 1.0000
-1.000 0.2408 0.01831 0.00832 -0.0696 0.7867 1.0000
-0.750 0.2639 0.01849 0.00825 -0.0688 0.7746 1.0000
-0.500 0.2872 0.01868 0.00823 -0.0680 0.7633 1.0000
-0.250 0.3112 0.01887 0.00821 -0.0672 0.7531 1.0000
0.000 0.3343 0.01910 0.00828 -0.0663 0.7425 1.0000
0.250 0.3568 0.01938 0.00840 -0.0654 0.7320 1.0000
0.500 0.3805 0.01963 0.00850 -0.0646 0.7228 1.0000
0.750 0.4047 0.01990 0.00865 -0.0639 0.7136 1.0000
1.000 0.4277 0.02023 0.00890 -0.0632 0.7039 1.0000
1.250 0.4525 0.02049 0.00904 -0.0626 0.6959 1.0000
1.500 0.4754 0.02086 0.00935 -0.0618 0.6866 1.0000
1.750 0.4989 0.02121 0.00966 -0.0611 0.6781 1.0000
2.000 0.5234 0.02153 0.00992 -0.0604 0.6702 1.0000
2.250 0.5457 0.02197 0.01036 -0.0597 0.6613 1.0000
2.500 0.5712 0.02225 0.01059 -0.0590 0.6544 1.0000
2.750 0.5925 0.02277 0.01116 -0.0582 0.6451 1.0000
3.000 0.6171 0.02312 0.01150 -0.0575 0.6380 1.0000
3.250 0.6391 0.02362 0.01204 -0.0567 0.6292 1.0000
3.500 0.6623 0.02407 0.01253 -0.0560 0.6214 1.0000
3.750 0.6856 0.02451 0.01304 -0.0552 0.6135 1.0000
4.000 0.7072 0.02506 0.01368 -0.0544 0.6049 1.0000
4.250 0.7321 0.02542 0.01407 -0.0537 0.5977 1.0000
4.500 0.7521 0.02607 0.01484 -0.0527 0.5882 1.0000
4.750 0.7771 0.02641 0.01524 -0.0519 0.5808 1.0000
5.000 0.7977 0.02700 0.01601 -0.0509 0.5710 1.0000
5.250 0.8186 0.02756 0.01670 -0.0499 0.5614 1.0000
5.500 0.8453 0.02772 0.01693 -0.0491 0.5534 1.0000
5.750 0.8639 0.02836 0.01774 -0.0479 0.5420 1.0000
6.000 0.8840 0.02887 0.01846 -0.0466 0.5307 1.0000
6.250 0.9059 0.02922 0.01896 -0.0454 0.5195 1.0000
6.500 0.9292 0.02940 0.01928 -0.0442 0.5081 1.0000
6.750 0.9526 0.02951 0.01953 -0.0430 0.4957 1.0000
7.000 0.9739 0.02968 0.01987 -0.0415 0.4819 1.0000
7.250 0.9925 0.02997 0.02040 -0.0398 0.4665 1.0000
7.500 1.0097 0.03027 0.02091 -0.0379 0.4495 1.0000
7.750 1.0274 0.03044 0.02128 -0.0360 0.4314 1.0000
8.000 1.0470 0.03036 0.02134 -0.0341 0.4120 1.0000
8.250 1.0596 0.03078 0.02196 -0.0317 0.3893 1.0000
8.500 1.0729 0.03107 0.02237 -0.0293 0.3644 1.0000
8.750 1.0836 0.03154 0.02298 -0.0268 0.3365 1.0000
9.000 1.0913 0.03225 0.02370 -0.0240 0.3058 1.0000
9.250 1.0955 0.03322 0.02460 -0.0211 0.2743 1.0000
9.500 1.0948 0.03456 0.02580 -0.0179 0.2454 1.0000
9.750 1.0912 0.03629 0.02740 -0.0149 0.2196 1.0000
10.000 1.0870 0.03836 0.02936 -0.0125 0.1971 1.0000
10.250 1.0821 0.04074 0.03164 -0.0106 0.1774 1.0000
10.500 1.0775 0.04334 0.03414 -0.0092 0.1603 1.0000
10.750 1.0738 0.04610 0.03690 -0.0082 0.1437 1.0000
11.000 1.0698 0.04903 0.03981 -0.0075 0.1287 1.0000
11.250 1.0661 0.05207 0.04283 -0.0069 0.1151 1.0000
11.500 1.0614 0.05533 0.04608 -0.0067 0.1021 1.0000
11.750 1.0563 0.05875 0.04949 -0.0068 0.0904 1.0000
12.000 1.0504 0.06238 0.05309 -0.0071 0.0797 1.0000
12.250 1.0457 0.06598 0.05674 -0.0076 0.0710 1.0000
12.500 1.0430 0.06957 0.06046 -0.0079 0.0627 1.0000
12.750 1.0395 0.07322 0.06408 -0.0083 0.0568 1.0000
13.000 1.0386 0.07681 0.06789 -0.0087 0.0513 1.0000
13.250 1.0367 0.08034 0.07138 -0.0091 0.0476 1.0000
13.500 1.0386 0.08395 0.07525 -0.0090 0.0446 1.0000
13.750 1.0377 0.08803 0.07960 -0.0096 0.0422 1.0000
14.000 1.0351 0.09235 0.08411 -0.0106 0.0405 1.0000
14.250 1.0314 0.09677 0.08867 -0.0119 0.0389 1.0000
14.500 1.0292 0.10095 0.09290 -0.0132 0.0374 1.0000
14.750 1.0221 0.10641 0.09852 -0.0153 0.0366 1.0000
15.000 1.0094 0.11327 0.10564 -0.0187 0.0363 1.0000
15.250 0.9959 0.12068 0.11327 -0.0225 0.0362 1.0000
15.500 0.9794 0.12924 0.12203 -0.0273 0.0362 1.0000
15.750 0.9638 0.13816 0.13108 -0.0323 0.0365 1.0000
16.000 0.9493 0.14737 0.14037 -0.0375 0.0368 1.0000
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Polar data table (+)
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