E186 (10.27%) (e186-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: E186 (10.27%) (e186-il) Reynolds number: 100,000 Max Cl/Cd: 45.28 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e186-il-100000-n5.txt Download as CSV file: xf-e186-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E186 (10.27%)
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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.6629 0.08872 0.08453 0.0142 1.0000 0.0265
-9.250 -0.6768 0.08010 0.07597 0.0069 1.0000 0.0258
-9.000 -0.7000 0.07140 0.06721 0.0008 1.0000 0.0251
-8.750 -0.7250 0.06476 0.06040 -0.0003 1.0000 0.0245
-8.500 -0.7446 0.05816 0.05346 -0.0002 1.0000 0.0240
-8.250 -0.7509 0.05313 0.04807 0.0008 1.0000 0.0238
-8.000 -0.7504 0.04872 0.04329 0.0020 1.0000 0.0238
-7.750 -0.7434 0.04527 0.03953 0.0031 1.0000 0.0242
-7.500 -0.7299 0.04301 0.03710 0.0038 1.0000 0.0254
-7.250 -0.7166 0.04024 0.03400 0.0049 1.0000 0.0266
-7.000 -0.7022 0.03709 0.03042 0.0061 1.0000 0.0274
-6.750 -0.6852 0.03392 0.02677 0.0073 1.0000 0.0276
-6.500 -0.6648 0.03116 0.02358 0.0081 1.0000 0.0278
-6.250 -0.6383 0.02868 0.02069 0.0081 0.9482 0.0282
-6.000 -0.6113 0.02672 0.01831 0.0084 0.9021 0.0289
-5.750 -0.5894 0.02523 0.01646 0.0099 0.8715 0.0296
-5.500 -0.5679 0.02395 0.01491 0.0115 0.8479 0.0304
-5.250 -0.5461 0.02297 0.01367 0.0130 0.8283 0.0317
-5.000 -0.5257 0.02178 0.01244 0.0144 0.8113 0.0346
-4.750 -0.5037 0.02096 0.01148 0.0156 0.7964 0.0373
-4.500 -0.4816 0.02012 0.01046 0.0170 0.7829 0.0395
-4.250 -0.4591 0.01940 0.00952 0.0183 0.7706 0.0421
-4.000 -0.4370 0.01859 0.00857 0.0196 0.7597 0.0473
-3.750 -0.4137 0.01783 0.00777 0.0206 0.7487 0.0607
-3.500 -0.3909 0.01699 0.00712 0.0215 0.7385 0.1079
-3.250 -0.3692 0.01607 0.00668 0.0224 0.7294 0.2069
-3.000 -0.3488 0.01507 0.00634 0.0235 0.7205 0.3471
-2.750 -0.3295 0.01390 0.00612 0.0252 0.7119 0.5475
-2.500 -0.2905 0.01315 0.00605 0.0242 0.7043 0.7456
-2.250 -0.2186 0.01333 0.00623 0.0169 0.6948 0.8559
-2.000 -0.1720 0.01362 0.00627 0.0140 0.6869 0.8989
-1.750 -0.1331 0.01390 0.00633 0.0124 0.6788 0.9284
-1.500 -0.0916 0.01412 0.00635 0.0099 0.6710 0.9501
-1.250 -0.0511 0.01430 0.00630 0.0075 0.6636 0.9693
-1.000 -0.0052 0.01435 0.00618 0.0038 0.6559 0.9842
-0.750 0.0414 0.01425 0.00590 -0.0002 0.6487 0.9965
-0.500 0.0726 0.01418 0.00571 -0.0013 0.6414 1.0000
-0.250 0.0961 0.01416 0.00557 -0.0007 0.6351 1.0000
0.000 0.1205 0.01417 0.00549 -0.0003 0.6283 1.0000
0.250 0.1447 0.01418 0.00542 0.0002 0.6219 1.0000
0.500 0.1693 0.01422 0.00539 0.0006 0.6157 1.0000
0.750 0.1941 0.01426 0.00538 0.0010 0.6091 1.0000
1.000 0.2186 0.01432 0.00536 0.0015 0.6036 1.0000
1.250 0.2440 0.01439 0.00544 0.0018 0.5966 1.0000
1.500 0.2686 0.01447 0.00545 0.0024 0.5913 1.0000
1.750 0.2942 0.01458 0.00559 0.0026 0.5844 1.0000
2.000 0.3191 0.01467 0.00568 0.0031 0.5785 1.0000
2.250 0.3446 0.01480 0.00583 0.0034 0.5722 1.0000
2.500 0.3698 0.01493 0.00597 0.0038 0.5657 1.0000
2.750 0.3949 0.01506 0.00612 0.0042 0.5597 1.0000
3.000 0.4204 0.01520 0.00635 0.0046 0.5525 1.0000
3.250 0.4454 0.01534 0.00651 0.0051 0.5461 1.0000
3.500 0.4708 0.01548 0.00673 0.0054 0.5380 1.0000
3.750 0.4960 0.01561 0.00692 0.0059 0.5299 1.0000
4.000 0.5208 0.01571 0.00707 0.0065 0.5215 1.0000
4.250 0.5462 0.01584 0.00735 0.0069 0.5112 1.0000
4.500 0.5711 0.01593 0.00753 0.0075 0.5010 1.0000
4.750 0.5959 0.01600 0.00766 0.0082 0.4902 1.0000
5.000 0.6207 0.01606 0.00781 0.0089 0.4779 1.0000
5.250 0.6455 0.01613 0.00800 0.0095 0.4638 1.0000
5.500 0.6705 0.01623 0.00829 0.0100 0.4470 1.0000
5.750 0.6952 0.01633 0.00853 0.0106 0.4276 1.0000
6.000 0.7196 0.01644 0.00874 0.0112 0.4051 1.0000
6.250 0.7438 0.01663 0.00902 0.0119 0.3753 1.0000
6.500 0.7671 0.01694 0.00933 0.0125 0.3340 1.0000
6.750 0.7888 0.01756 0.00983 0.0131 0.2772 1.0000
7.000 0.8079 0.01868 0.01065 0.0136 0.2125 1.0000
7.250 0.8237 0.02032 0.01187 0.0140 0.1429 1.0000
7.500 0.8377 0.02205 0.01315 0.0146 0.0841 1.0000
7.750 0.8521 0.02356 0.01448 0.0156 0.0537 1.0000
8.000 0.8649 0.02516 0.01606 0.0169 0.0371 1.0000
8.250 0.8753 0.02688 0.01782 0.0185 0.0302 1.0000
8.500 0.8864 0.02835 0.01940 0.0200 0.0256 1.0000
8.750 0.8929 0.03010 0.02125 0.0217 0.0229 1.0000
9.000 0.9021 0.03152 0.02282 0.0235 0.0208 1.0000
9.250 0.9085 0.03312 0.02455 0.0254 0.0195 1.0000
9.500 0.9138 0.03478 0.02633 0.0272 0.0186 1.0000
9.750 0.9161 0.03643 0.02806 0.0293 0.0181 1.0000
10.000 0.9175 0.03827 0.02998 0.0312 0.0175 1.0000
10.250 0.9206 0.04022 0.03202 0.0327 0.0170 1.0000
10.500 0.9247 0.04235 0.03424 0.0341 0.0166 1.0000
10.750 0.9289 0.04485 0.03684 0.0355 0.0161 1.0000
11.000 0.9333 0.04729 0.03949 0.0365 0.0159 1.0000
11.250 0.9354 0.04996 0.04238 0.0372 0.0158 1.0000
11.500 0.9342 0.05305 0.04572 0.0376 0.0156 1.0000
11.750 0.9302 0.05644 0.04934 0.0376 0.0155 1.0000
12.000 0.9238 0.06014 0.05327 0.0371 0.0155 1.0000
12.250 0.9142 0.06432 0.05767 0.0360 0.0154 1.0000
12.500 0.9026 0.06892 0.06249 0.0345 0.0153 1.0000
12.750 0.8893 0.07392 0.06769 0.0323 0.0152 1.0000
13.000 0.8750 0.07937 0.07331 0.0297 0.0154 1.0000
13.250 0.8592 0.08537 0.07948 0.0266 0.0155 1.0000
13.500 0.8413 0.09216 0.08642 0.0228 0.0155 1.0000
13.750 0.8230 0.09968 0.09407 0.0185 0.0157 1.0000
14.000 0.8053 0.10776 0.10226 0.0138 0.0158 1.0000
14.250 0.7882 0.11636 0.11093 0.0090 0.0160 1.0000
14.500 0.7705 0.12583 0.12044 0.0040 0.0162 1.0000
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Polar data table (+)
Polar graphs
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