E180 (8.59%) (e180-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: E180 (8.59%) (e180-il) Reynolds number: 200,000 Max Cl/Cd: 65.96 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e180-il-200000-n5.txt Download as CSV file: xf-e180-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E180 (8.59%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5157 0.09667 0.09339 0.0018 1.0000 0.0144
-8.750 -0.5131 0.09281 0.08956 0.0001 1.0000 0.0139
-8.500 -0.5114 0.08876 0.08555 -0.0021 1.0000 0.0133
-8.250 -0.5114 0.08441 0.08124 -0.0048 1.0000 0.0129
-8.000 -0.5134 0.07979 0.07669 -0.0079 1.0000 0.0125
-7.750 -0.5177 0.07502 0.07198 -0.0117 1.0000 0.0122
-7.500 -0.5179 0.06903 0.06600 -0.0176 1.0000 0.0117
-7.250 -0.5166 0.06136 0.05828 -0.0242 1.0000 0.0111
-7.000 -0.5158 0.04875 0.04536 -0.0306 1.0000 0.0099
-6.500 -0.4842 0.03698 0.03272 -0.0353 0.9164 0.0095
-6.250 -0.4715 0.03253 0.02772 -0.0348 0.8915 0.0095
-6.000 -0.4561 0.02884 0.02344 -0.0337 0.8724 0.0095
-5.750 -0.4376 0.02591 0.01996 -0.0326 0.8563 0.0095
-5.500 -0.4178 0.02306 0.01655 -0.0314 0.8422 0.0098
-5.250 -0.3966 0.02092 0.01402 -0.0305 0.8294 0.0105
-5.000 -0.3729 0.01998 0.01283 -0.0298 0.8177 0.0118
-4.750 -0.3482 0.01874 0.01130 -0.0291 0.8065 0.0128
-4.500 -0.3233 0.01738 0.00968 -0.0283 0.7962 0.0132
-4.250 -0.2984 0.01625 0.00834 -0.0275 0.7869 0.0138
-4.000 -0.2733 0.01535 0.00725 -0.0268 0.7776 0.0145
-3.750 -0.2476 0.01462 0.00634 -0.0262 0.7687 0.0153
-3.500 -0.2223 0.01389 0.00547 -0.0257 0.7607 0.0175
-3.250 -0.1960 0.01338 0.00488 -0.0253 0.7523 0.0233
-3.000 -0.1700 0.01279 0.00427 -0.0248 0.7449 0.0405
-2.750 -0.1439 0.01231 0.00388 -0.0245 0.7373 0.0748
-2.500 -0.1184 0.01176 0.00361 -0.0243 0.7303 0.1428
-2.250 -0.0926 0.01131 0.00334 -0.0241 0.7232 0.2122
-2.000 -0.0670 0.01089 0.00313 -0.0238 0.7166 0.2918
-1.750 -0.0422 0.01039 0.00297 -0.0234 0.7098 0.3979
-1.500 -0.0188 0.00986 0.00284 -0.0225 0.7037 0.5256
-1.250 0.0030 0.00928 0.00276 -0.0210 0.6971 0.6700
-0.750 0.0906 0.00871 0.00267 -0.0262 0.6849 0.9518
-0.500 0.1356 0.00875 0.00255 -0.0298 0.6791 0.9877
-0.250 0.1733 0.00876 0.00245 -0.0319 0.6727 1.0000
0.000 0.1989 0.00881 0.00239 -0.0315 0.6666 1.0000
0.250 0.2247 0.00887 0.00236 -0.0311 0.6608 1.0000
0.500 0.2506 0.00892 0.00234 -0.0307 0.6545 1.0000
0.750 0.2764 0.00900 0.00232 -0.0303 0.6493 1.0000
1.000 0.3027 0.00906 0.00236 -0.0300 0.6426 1.0000
1.250 0.3287 0.00915 0.00237 -0.0296 0.6370 1.0000
1.500 0.3550 0.00922 0.00244 -0.0293 0.6304 1.0000
1.750 0.3811 0.00931 0.00249 -0.0289 0.6242 1.0000
2.000 0.4073 0.00940 0.00256 -0.0286 0.6173 1.0000
2.250 0.4335 0.00948 0.00264 -0.0282 0.6099 1.0000
2.500 0.4598 0.00957 0.00273 -0.0279 0.6016 1.0000
2.750 0.4858 0.00966 0.00279 -0.0274 0.5930 1.0000
3.000 0.5122 0.00974 0.00289 -0.0271 0.5826 1.0000
3.250 0.5385 0.00982 0.00302 -0.0268 0.5721 1.0000
3.500 0.5647 0.00992 0.00313 -0.0264 0.5613 1.0000
3.750 0.5909 0.01002 0.00324 -0.0260 0.5493 1.0000
4.000 0.6171 0.01012 0.00337 -0.0256 0.5356 1.0000
4.250 0.6432 0.01024 0.00355 -0.0253 0.5199 1.0000
4.500 0.6692 0.01037 0.00371 -0.0249 0.5022 1.0000
4.750 0.6945 0.01054 0.00384 -0.0244 0.4711 1.0000
5.000 0.7183 0.01089 0.00397 -0.0237 0.4101 1.0000
5.250 0.7405 0.01155 0.00427 -0.0231 0.3292 1.0000
5.500 0.7620 0.01242 0.00482 -0.0226 0.2535 1.0000
5.750 0.7828 0.01342 0.00546 -0.0220 0.1809 1.0000
6.000 0.8043 0.01428 0.00609 -0.0215 0.1291 1.0000
6.250 0.8253 0.01521 0.00678 -0.0210 0.0822 1.0000
6.500 0.8454 0.01625 0.00759 -0.0203 0.0421 1.0000
6.750 0.8664 0.01714 0.00842 -0.0195 0.0268 1.0000
7.000 0.8882 0.01787 0.00927 -0.0188 0.0229 1.0000
7.250 0.9086 0.01879 0.01027 -0.0180 0.0204 1.0000
7.500 0.9289 0.01965 0.01127 -0.0171 0.0194 1.0000
7.750 0.9483 0.02058 0.01234 -0.0161 0.0186 1.0000
8.000 0.9664 0.02163 0.01352 -0.0151 0.0180 1.0000
8.250 0.9834 0.02278 0.01480 -0.0138 0.0174 1.0000
8.500 1.0003 0.02391 0.01602 -0.0127 0.0165 1.0000
8.750 1.0168 0.02501 0.01721 -0.0116 0.0154 1.0000
9.000 1.0314 0.02637 0.01870 -0.0103 0.0146 1.0000
9.250 1.0448 0.02803 0.02047 -0.0089 0.0141 1.0000
9.500 1.0582 0.03007 0.02265 -0.0074 0.0137 1.0000
9.750 1.0723 0.03236 0.02511 -0.0061 0.0134 1.0000
10.000 1.0862 0.03425 0.02724 -0.0049 0.0132 1.0000
10.250 1.0978 0.03626 0.02951 -0.0035 0.0129 1.0000
10.500 1.1053 0.03814 0.03166 -0.0017 0.0124 1.0000
10.750 1.1088 0.04005 0.03381 0.0002 0.0118 1.0000
11.000 1.1097 0.04228 0.03629 0.0019 0.0114 1.0000
11.250 1.1075 0.04499 0.03925 0.0032 0.0111 1.0000
11.500 1.1026 0.04801 0.04256 0.0041 0.0108 1.0000
11.750 1.0954 0.05139 0.04619 0.0045 0.0107 1.0000
12.000 1.0854 0.05522 0.05027 0.0044 0.0106 1.0000
12.250 1.0734 0.05951 0.05479 0.0035 0.0105 1.0000
12.500 1.0595 0.06431 0.05981 0.0020 0.0104 1.0000
12.750 1.0432 0.06981 0.06553 -0.0002 0.0104 1.0000
13.000 1.0244 0.07616 0.07209 -0.0034 0.0104 1.0000
13.250 1.0052 0.08313 0.07925 -0.0075 0.0105 1.0000
13.500 0.9827 0.09153 0.08783 -0.0127 0.0107 1.0000
13.750 0.9586 0.10148 0.09790 -0.0192 0.0109 1.0000
14.000 0.9299 0.11442 0.11098 -0.0275 0.0112 1.0000
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Polar data table (+)
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