E186 (10.27%) (e186-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: E186 (10.27%) (e186-il) Reynolds number: 500,000 Max Cl/Cd: 71.14 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e186-il-500000-n5.txt Download as CSV file: xf-e186-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.7399 0.08447 0.08264 0.0207 1.0000 0.0077
-10.000 -0.8510 0.05459 0.05251 0.0018 1.0000 0.0071
-9.750 -0.8878 0.04824 0.04587 0.0047 1.0000 0.0071
-9.500 -0.9010 0.04343 0.04076 0.0069 1.0000 0.0072
-9.250 -0.9069 0.03895 0.03592 0.0092 1.0000 0.0073
-9.000 -0.9071 0.03612 0.03266 0.0124 0.8781 0.0076
-8.750 -0.9035 0.03326 0.02935 0.0154 0.8404 0.0078
-8.500 -0.8944 0.03063 0.02628 0.0177 0.8130 0.0081
-8.250 -0.8813 0.02833 0.02357 0.0196 0.7903 0.0084
-8.000 -0.8643 0.02657 0.02146 0.0211 0.7705 0.0088
-7.750 -0.8442 0.02537 0.01998 0.0223 0.7528 0.0093
-7.500 -0.8228 0.02437 0.01871 0.0233 0.7372 0.0096
-7.250 -0.8007 0.02345 0.01754 0.0242 0.7229 0.0098
-7.000 -0.7810 0.02148 0.01522 0.0254 0.7106 0.0101
-6.750 -0.7607 0.01956 0.01302 0.0266 0.6994 0.0105
-6.500 -0.7380 0.01842 0.01170 0.0275 0.6888 0.0108
-6.250 -0.7143 0.01752 0.01066 0.0282 0.6783 0.0111
-6.000 -0.6902 0.01672 0.00973 0.0288 0.6689 0.0114
-5.750 -0.6657 0.01607 0.00897 0.0295 0.6604 0.0118
-5.500 -0.6408 0.01549 0.00829 0.0300 0.6516 0.0123
-5.250 -0.6160 0.01489 0.00757 0.0306 0.6440 0.0128
-5.000 -0.5913 0.01427 0.00684 0.0313 0.6364 0.0131
-4.750 -0.5664 0.01371 0.00618 0.0319 0.6297 0.0135
-4.500 -0.5412 0.01322 0.00558 0.0325 0.6226 0.0139
-4.250 -0.5156 0.01280 0.00507 0.0330 0.6164 0.0143
-4.000 -0.4897 0.01243 0.00461 0.0335 0.6100 0.0148
-3.750 -0.4635 0.01212 0.00420 0.0339 0.6042 0.0151
-3.500 -0.4371 0.01181 0.00382 0.0343 0.5981 0.0155
-3.250 -0.4108 0.01151 0.00343 0.0346 0.5925 0.0163
-3.000 -0.3841 0.01126 0.00311 0.0350 0.5872 0.0177
-2.750 -0.3573 0.01103 0.00285 0.0353 0.5815 0.0199
-2.500 -0.3304 0.01085 0.00261 0.0355 0.5765 0.0224
-2.250 -0.3045 0.01048 0.00237 0.0359 0.5714 0.0530
-2.000 -0.2787 0.01012 0.00217 0.0363 0.5662 0.0976
-1.750 -0.2529 0.00981 0.00200 0.0366 0.5614 0.1445
-1.500 -0.2271 0.00948 0.00185 0.0370 0.5564 0.1977
-1.250 -0.2024 0.00903 0.00171 0.0374 0.5515 0.2843
-1.000 -0.1782 0.00859 0.00159 0.0380 0.5469 0.3781
-0.750 -0.1580 0.00786 0.00147 0.0394 0.5422 0.5356
-0.500 -0.1426 0.00705 0.00137 0.0420 0.5378 0.7140
-0.250 -0.1159 0.00654 0.00136 0.0427 0.5334 0.8475
0.000 -0.0362 0.00662 0.00156 0.0316 0.5266 0.9135
0.250 0.0059 0.00679 0.00167 0.0288 0.5215 0.9310
0.500 0.0394 0.00692 0.00177 0.0278 0.5165 0.9428
0.750 0.0718 0.00705 0.00186 0.0269 0.5112 0.9526
1.000 0.1035 0.00718 0.00193 0.0262 0.5064 0.9612
1.250 0.1341 0.00729 0.00202 0.0258 0.5012 0.9687
1.500 0.1697 0.00739 0.00209 0.0241 0.4958 0.9731
1.750 0.2056 0.00749 0.00216 0.0224 0.4905 0.9778
2.000 0.2373 0.00760 0.00226 0.0217 0.4846 0.9829
2.500 0.3126 0.00768 0.00231 0.0174 0.4695 0.9883
2.750 0.3473 0.00773 0.00234 0.0158 0.4612 0.9912
3.000 0.3806 0.00780 0.00239 0.0146 0.4521 0.9938
3.250 0.4151 0.00781 0.00241 0.0131 0.4417 0.9955
3.500 0.4490 0.00783 0.00242 0.0117 0.4309 0.9973
3.750 0.4823 0.00787 0.00245 0.0104 0.4195 0.9990
4.000 0.5135 0.00793 0.00250 0.0096 0.4056 1.0000
4.250 0.5396 0.00803 0.00259 0.0099 0.3913 1.0000
4.500 0.5657 0.00814 0.00269 0.0101 0.3748 1.0000
4.750 0.5919 0.00832 0.00281 0.0103 0.3508 1.0000
5.000 0.6178 0.00873 0.00300 0.0102 0.2942 1.0000
5.250 0.6434 0.00956 0.00343 0.0098 0.2056 1.0000
5.500 0.6689 0.01007 0.00377 0.0098 0.1645 1.0000
5.750 0.6942 0.01061 0.00415 0.0097 0.1259 1.0000
6.000 0.7187 0.01134 0.00464 0.0097 0.0787 1.0000
6.250 0.7431 0.01193 0.00509 0.0098 0.0498 1.0000
6.500 0.7672 0.01252 0.00558 0.0100 0.0282 1.0000
6.750 0.7907 0.01322 0.00620 0.0102 0.0113 1.0000
7.000 0.8146 0.01370 0.00671 0.0106 0.0090 1.0000
7.250 0.8380 0.01424 0.00731 0.0111 0.0076 1.0000
7.500 0.8610 0.01481 0.00796 0.0116 0.0068 1.0000
7.750 0.8839 0.01532 0.00854 0.0121 0.0062 1.0000
8.000 0.9060 0.01591 0.00922 0.0127 0.0059 1.0000
8.250 0.9274 0.01657 0.00998 0.0133 0.0056 1.0000
8.500 0.9478 0.01730 0.01080 0.0141 0.0052 1.0000
8.750 0.9673 0.01809 0.01167 0.0149 0.0050 1.0000
9.000 0.9856 0.01897 0.01263 0.0158 0.0048 1.0000
9.250 1.0018 0.01999 0.01375 0.0169 0.0046 1.0000
9.500 1.0158 0.02113 0.01499 0.0182 0.0044 1.0000
9.750 1.0282 0.02230 0.01626 0.0197 0.0043 1.0000
10.000 1.0314 0.02420 0.01830 0.0220 0.0041 1.0000
10.250 1.0341 0.02597 0.02020 0.0243 0.0040 1.0000
10.500 1.0332 0.02747 0.02180 0.0270 0.0040 1.0000
10.750 1.0312 0.02895 0.02340 0.0294 0.0039 1.0000
11.000 1.0325 0.03062 0.02518 0.0309 0.0039 1.0000
11.250 1.0340 0.03252 0.02719 0.0320 0.0039 1.0000
11.500 1.0351 0.03465 0.02945 0.0328 0.0038 1.0000
11.750 1.0367 0.03683 0.03175 0.0334 0.0038 1.0000
12.000 1.0368 0.03927 0.03432 0.0338 0.0038 1.0000
12.250 1.0356 0.04196 0.03716 0.0339 0.0038 1.0000
12.500 1.0333 0.04487 0.04021 0.0339 0.0038 1.0000
12.750 1.0301 0.04794 0.04342 0.0335 0.0037 1.0000
13.000 1.0252 0.05133 0.04696 0.0329 0.0037 1.0000
13.250 1.0189 0.05502 0.05079 0.0321 0.0037 1.0000
13.500 1.0106 0.05910 0.05503 0.0308 0.0037 1.0000
13.750 1.0025 0.06332 0.05940 0.0293 0.0037 1.0000
14.000 0.9920 0.06808 0.06430 0.0275 0.0037 1.0000
14.250 0.9793 0.07353 0.06990 0.0251 0.0037 1.0000
14.500 0.9667 0.07933 0.07585 0.0223 0.0037 1.0000
14.750 0.9549 0.08524 0.08189 0.0193 0.0037 1.0000
15.000 0.9404 0.09203 0.08882 0.0158 0.0037 1.0000
15.250 0.9205 0.10022 0.09716 0.0116 0.0037 1.0000
15.500 0.9050 0.10790 0.10496 0.0077 0.0037 1.0000
15.750 0.8855 0.11683 0.11401 0.0031 0.0038 1.0000
16.000 0.8658 0.12639 0.12369 -0.0017 0.0038 1.0000
16.250 0.8408 0.13770 0.13511 -0.0071 0.0039 1.0000
|
Polar data table (+)
Polar graphs
<< Back to E186 (10.27%) (e186-il)