GOE 240 (KOLLER) AIRFOIL (goe240-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 240 (KOLLER) AIRFOIL (goe240-il) Reynolds number: 1,000,000 Max Cl/Cd: 99.41 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe240-il-1000000-n5.txt Download as CSV file: xf-goe240-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 240 (KOLLER) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3181 0.09509 0.09347 -0.0326 0.9728 0.0052
-8.750 -0.3174 0.09009 0.08847 -0.0351 0.9628 0.0055
-8.500 -0.3102 0.08751 0.08588 -0.0364 0.9516 0.0056
-8.250 -0.3029 0.08506 0.08341 -0.0375 0.9363 0.0058
-8.000 -0.2987 0.08265 0.08087 -0.0380 0.8792 0.0059
-7.750 -0.2914 0.07994 0.07791 -0.0399 0.8286 0.0061
-7.500 -0.2789 0.07610 0.07398 -0.0443 0.8124 0.0065
-7.250 -0.2647 0.07074 0.06855 -0.0508 0.8019 0.0070
-6.000 -0.1422 0.04382 0.04120 -0.0855 0.7705 0.0107
-5.500 -0.0773 0.02849 0.02525 -0.0987 0.7611 0.0141
-5.250 -0.0504 0.02769 0.02439 -0.0993 0.7563 0.0144
-5.000 -0.0230 0.01523 0.01077 -0.1031 0.7523 0.0182
-4.750 0.0041 0.01412 0.00941 -0.1033 0.7478 0.0187
-4.500 0.0317 0.01362 0.00883 -0.1034 0.7438 0.0191
-4.250 0.0596 0.01341 0.00858 -0.1035 0.7396 0.0194
-4.000 0.0873 0.01315 0.00825 -0.1036 0.7345 0.0199
-3.750 0.1151 0.01262 0.00760 -0.1036 0.7292 0.0203
-3.500 0.1430 0.01205 0.00691 -0.1037 0.7225 0.0208
-3.250 0.1708 0.01158 0.00629 -0.1037 0.7160 0.0214
-3.000 0.1989 0.01114 0.00574 -0.1038 0.7093 0.0221
-2.750 0.2269 0.01069 0.00517 -0.1037 0.7026 0.0226
-2.500 0.2550 0.01028 0.00465 -0.1038 0.6947 0.0229
-2.250 0.2829 0.00994 0.00420 -0.1037 0.6852 0.0231
-2.000 0.3109 0.00964 0.00380 -0.1037 0.6744 0.0233
-1.750 0.3389 0.00935 0.00344 -0.1037 0.6646 0.0235
-1.500 0.3668 0.00909 0.00310 -0.1036 0.6535 0.0236
-1.250 0.3945 0.00891 0.00282 -0.1035 0.6354 0.0238
-1.000 0.4213 0.00891 0.00265 -0.1033 0.5969 0.0240
-0.750 0.4477 0.00892 0.00246 -0.1030 0.5555 0.0241
-0.500 0.4749 0.00884 0.00226 -0.1029 0.5344 0.0241
-0.250 0.5024 0.00875 0.00210 -0.1028 0.5198 0.0242
0.000 0.5298 0.00861 0.00188 -0.1027 0.5043 0.0245
0.250 0.5573 0.00846 0.00163 -0.1027 0.4882 0.0254
0.500 0.5849 0.00841 0.00153 -0.1026 0.4746 0.0263
0.750 0.6125 0.00841 0.00149 -0.1026 0.4611 0.0271
1.000 0.6400 0.00845 0.00147 -0.1025 0.4437 0.0277
1.250 0.6661 0.00868 0.00150 -0.1023 0.3975 0.0283
1.500 0.6911 0.00908 0.00161 -0.1019 0.3389 0.0288
1.750 0.7177 0.00925 0.00168 -0.1017 0.3159 0.0292
2.000 0.7445 0.00941 0.00175 -0.1016 0.2982 0.0296
2.250 0.7714 0.00956 0.00183 -0.1014 0.2803 0.0304
2.500 0.7982 0.00971 0.00191 -0.1013 0.2638 0.0311
2.750 0.8247 0.00989 0.00202 -0.1011 0.2437 0.0316
3.000 0.8506 0.01016 0.00216 -0.1009 0.2157 0.0320
3.250 0.8754 0.01056 0.00238 -0.1005 0.1772 0.0370
3.750 0.9269 0.01105 0.00281 -0.0999 0.1396 0.0876
4.000 0.9534 0.01110 0.00302 -0.0999 0.1310 0.1987
4.500 1.0021 0.01008 0.00353 -0.0990 0.1179 1.0000
4.750 1.0279 0.01035 0.00373 -0.0987 0.1087 1.0000
5.000 1.0532 0.01067 0.00396 -0.0984 0.0951 1.0000
5.250 1.0759 0.01128 0.00437 -0.0977 0.0579 1.0000
5.500 1.1014 0.01156 0.00463 -0.0974 0.0519 1.0000
5.750 1.1272 0.01178 0.00487 -0.0971 0.0494 1.0000
6.000 1.1526 0.01204 0.00513 -0.0968 0.0463 1.0000
6.250 1.1773 0.01237 0.00545 -0.0964 0.0416 1.0000
6.500 1.2021 0.01267 0.00573 -0.0960 0.0357 1.0000
6.750 1.2241 0.01330 0.00623 -0.0951 0.0153 1.0000
7.000 1.2485 0.01362 0.00658 -0.0947 0.0124 1.0000
7.250 1.2723 0.01401 0.00700 -0.0941 0.0106 1.0000
7.500 1.2955 0.01444 0.00746 -0.0934 0.0089 1.0000
7.750 1.3192 0.01479 0.00785 -0.0929 0.0082 1.0000
8.000 1.3423 0.01519 0.00828 -0.0922 0.0074 1.0000
8.250 1.3647 0.01564 0.00875 -0.0915 0.0068 1.0000
8.500 1.3858 0.01623 0.00938 -0.0905 0.0060 1.0000
8.750 1.4078 0.01667 0.00986 -0.0897 0.0058 1.0000
9.000 1.4293 0.01714 0.01039 -0.0889 0.0054 1.0000
9.250 1.4503 0.01763 0.01091 -0.0880 0.0050 1.0000
9.500 1.4705 0.01816 0.01147 -0.0869 0.0047 1.0000
9.750 1.4896 0.01876 0.01212 -0.0857 0.0044 1.0000
10.000 1.5060 0.01956 0.01299 -0.0842 0.0040 1.0000
10.250 1.5233 0.02023 0.01372 -0.0827 0.0039 1.0000
10.500 1.5397 0.02090 0.01447 -0.0811 0.0038 1.0000
10.750 1.5531 0.02162 0.01526 -0.0790 0.0036 1.0000
11.000 1.5650 0.02240 0.01611 -0.0768 0.0035 1.0000
11.250 1.5759 0.02325 0.01704 -0.0745 0.0034 1.0000
11.500 1.5860 0.02418 0.01804 -0.0722 0.0033 1.0000
11.750 1.5956 0.02517 0.01911 -0.0700 0.0031 1.0000
12.000 1.6042 0.02627 0.02029 -0.0679 0.0030 1.0000
12.250 1.6124 0.02743 0.02154 -0.0659 0.0029 1.0000
12.500 1.6197 0.02873 0.02291 -0.0640 0.0029 1.0000
12.750 1.6258 0.03019 0.02445 -0.0622 0.0028 1.0000
13.000 1.6293 0.03198 0.02634 -0.0604 0.0027 1.0000
13.250 1.6278 0.03435 0.02883 -0.0587 0.0025 1.0000
13.500 1.6264 0.03689 0.03149 -0.0573 0.0025 1.0000
13.750 1.6290 0.03911 0.03381 -0.0564 0.0024 1.0000
14.000 1.6302 0.04156 0.03637 -0.0555 0.0024 1.0000
14.250 1.6286 0.04440 0.03933 -0.0548 0.0024 1.0000
14.500 1.6256 0.04748 0.04253 -0.0543 0.0023 1.0000
14.750 1.6205 0.05096 0.04614 -0.0541 0.0023 1.0000
15.000 1.6142 0.05472 0.05003 -0.0541 0.0023 1.0000
15.250 1.6059 0.05893 0.05436 -0.0544 0.0022 1.0000
15.500 1.5966 0.06353 0.05909 -0.0551 0.0022 1.0000
15.750 1.5863 0.06850 0.06420 -0.0562 0.0022 1.0000
16.000 1.5745 0.07384 0.06967 -0.0576 0.0022 1.0000
16.250 1.5620 0.07946 0.07542 -0.0592 0.0022 1.0000
16.500 1.5478 0.08548 0.08157 -0.0611 0.0021 1.0000
16.750 1.5326 0.09174 0.08796 -0.0632 0.0021 1.0000
17.000 1.5163 0.09834 0.09469 -0.0655 0.0021 1.0000
17.250 1.5007 0.10499 0.10146 -0.0680 0.0021 1.0000
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Polar data table (+)
Polar graphs
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