GOE 264 AIRFOIL (goe264-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 264 AIRFOIL (goe264-il) Reynolds number: 1,000,000 Max Cl/Cd: 121.8 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe264-il-1000000-n5.txt Download as CSV file: xf-goe264-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 264 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3396 0.09584 0.09431 -0.0234 0.9834 0.0050
-8.500 -0.3328 0.09164 0.09009 -0.0263 0.9683 0.0053
-8.000 -0.3386 0.07665 0.07505 -0.0389 0.9365 0.0066
-7.750 -0.3230 0.07382 0.07219 -0.0421 0.9224 0.0069
-7.500 -0.3057 0.07057 0.06888 -0.0461 0.9077 0.0072
-7.000 -0.2217 0.01374 0.00980 -0.1105 0.8892 0.0113
-6.750 -0.1938 0.01213 0.00788 -0.1112 0.8760 0.0131
-6.500 -0.1659 0.01135 0.00695 -0.1115 0.8625 0.0168
-6.250 -0.1380 0.01120 0.00676 -0.1115 0.8483 0.0195
-6.000 -0.1101 0.01133 0.00686 -0.1113 0.8342 0.0218
-5.750 -0.0820 0.01131 0.00673 -0.1112 0.8203 0.0236
-5.500 -0.0538 0.01128 0.00661 -0.1112 0.8056 0.0245
-5.250 -0.0255 0.01119 0.00640 -0.1112 0.7895 0.0249
-5.000 0.0031 0.01086 0.00590 -0.1114 0.7706 0.0257
-4.750 0.0314 0.01078 0.00571 -0.1115 0.7464 0.0268
-4.500 0.0595 0.01096 0.00577 -0.1114 0.7117 0.0276
-4.250 0.0871 0.01142 0.00612 -0.1113 0.6709 0.0285
-4.000 0.1154 0.01150 0.00605 -0.1113 0.6432 0.0294
-3.750 0.1444 0.01109 0.00544 -0.1117 0.6251 0.0299
-3.500 0.1734 0.01067 0.00483 -0.1120 0.6108 0.0302
-3.250 0.2024 0.01032 0.00433 -0.1122 0.5982 0.0306
-3.000 0.2313 0.01000 0.00389 -0.1125 0.5868 0.0309
-2.750 0.2603 0.00975 0.00353 -0.1127 0.5763 0.0313
-2.500 0.2891 0.00961 0.00330 -0.1129 0.5652 0.0319
-2.250 0.3179 0.00942 0.00301 -0.1131 0.5539 0.0322
-2.000 0.3468 0.00928 0.00279 -0.1133 0.5427 0.0325
-1.750 0.3755 0.00919 0.00262 -0.1134 0.5307 0.0328
-1.500 0.4045 0.00894 0.00229 -0.1137 0.5177 0.0341
-1.250 0.4333 0.00886 0.00214 -0.1139 0.5044 0.0353
-1.000 0.4619 0.00884 0.00207 -0.1140 0.4913 0.0363
-0.750 0.4905 0.00884 0.00200 -0.1142 0.4767 0.0372
-0.500 0.5190 0.00885 0.00194 -0.1143 0.4633 0.0381
-0.250 0.5476 0.00885 0.00189 -0.1145 0.4509 0.0390
0.000 0.5761 0.00888 0.00185 -0.1146 0.4370 0.0400
0.250 0.6044 0.00894 0.00183 -0.1148 0.4203 0.0409
0.500 0.6327 0.00900 0.00183 -0.1149 0.4068 0.0417
0.750 0.6612 0.00903 0.00182 -0.1150 0.3973 0.0426
1.000 0.6897 0.00903 0.00179 -0.1152 0.3891 0.0457
1.250 0.7181 0.00907 0.00182 -0.1154 0.3808 0.0488
1.500 0.7465 0.00911 0.00185 -0.1155 0.3737 0.0514
1.750 0.7747 0.00918 0.00189 -0.1156 0.3653 0.0532
2.000 0.8030 0.00923 0.00193 -0.1157 0.3581 0.0555
2.500 0.8595 0.00934 0.00208 -0.1160 0.3433 0.0786
2.750 0.8876 0.00940 0.00219 -0.1161 0.3366 0.1105
3.000 0.9157 0.00946 0.00229 -0.1163 0.3312 0.1302
3.250 0.9437 0.00955 0.00240 -0.1164 0.3239 0.1436
3.500 0.9716 0.00965 0.00252 -0.1165 0.3175 0.1555
3.750 0.9995 0.00972 0.00264 -0.1166 0.3122 0.1734
4.000 1.0274 0.00981 0.00280 -0.1167 0.3061 0.2187
4.500 1.0779 0.00885 0.00322 -0.1162 0.2844 1.0000
4.750 1.1050 0.00908 0.00339 -0.1162 0.2697 1.0000
5.000 1.1316 0.00940 0.00360 -0.1161 0.2492 1.0000
5.250 1.1575 0.00983 0.00386 -0.1160 0.2199 1.0000
5.500 1.1790 0.01100 0.00455 -0.1154 0.1296 1.0000
5.750 1.2032 0.01167 0.00506 -0.1151 0.0982 1.0000
6.000 1.2262 0.01252 0.00565 -0.1146 0.0462 1.0000
6.250 1.2506 0.01308 0.00611 -0.1142 0.0260 1.0000
6.500 1.2755 0.01355 0.00652 -0.1138 0.0154 1.0000
6.750 1.3006 0.01395 0.00693 -0.1135 0.0114 1.0000
7.000 1.3259 0.01428 0.00729 -0.1132 0.0105 1.0000
7.250 1.3506 0.01468 0.00771 -0.1129 0.0092 1.0000
7.500 1.3746 0.01517 0.00821 -0.1124 0.0078 1.0000
7.750 1.3988 0.01558 0.00865 -0.1120 0.0072 1.0000
8.000 1.4228 0.01600 0.00912 -0.1115 0.0066 1.0000
8.250 1.4461 0.01648 0.00963 -0.1110 0.0060 1.0000
8.500 1.4685 0.01703 0.01020 -0.1103 0.0055 1.0000
8.750 1.4898 0.01768 0.01092 -0.1094 0.0051 1.0000
9.000 1.5117 0.01822 0.01151 -0.1087 0.0049 1.0000
9.250 1.5327 0.01881 0.01215 -0.1078 0.0046 1.0000
9.500 1.5532 0.01941 0.01280 -0.1068 0.0043 1.0000
9.750 1.5731 0.02001 0.01347 -0.1058 0.0040 1.0000
10.000 1.5920 0.02066 0.01416 -0.1047 0.0038 1.0000
10.250 1.6088 0.02146 0.01501 -0.1032 0.0036 1.0000
10.500 1.6212 0.02254 0.01618 -0.1010 0.0034 1.0000
10.750 1.6351 0.02336 0.01708 -0.0991 0.0033 1.0000
11.000 1.6465 0.02424 0.01805 -0.0968 0.0032 1.0000
11.250 1.6534 0.02521 0.01911 -0.0938 0.0031 1.0000
11.500 1.6589 0.02633 0.02031 -0.0908 0.0030 1.0000
11.750 1.6637 0.02762 0.02170 -0.0880 0.0029 1.0000
12.000 1.6680 0.02906 0.02324 -0.0855 0.0029 1.0000
12.250 1.6716 0.03069 0.02498 -0.0833 0.0028 1.0000
12.500 1.6742 0.03252 0.02692 -0.0812 0.0027 1.0000
12.750 1.6758 0.03461 0.02911 -0.0795 0.0027 1.0000
13.000 1.6775 0.03685 0.03145 -0.0781 0.0026 1.0000
13.250 1.6771 0.03944 0.03415 -0.0770 0.0025 1.0000
13.500 1.6769 0.04219 0.03701 -0.0762 0.0025 1.0000
13.750 1.6753 0.04526 0.04019 -0.0757 0.0024 1.0000
14.000 1.6725 0.04866 0.04369 -0.0755 0.0024 1.0000
14.250 1.6684 0.05239 0.04755 -0.0756 0.0024 1.0000
14.500 1.6636 0.05634 0.05160 -0.0760 0.0023 1.0000
14.750 1.6572 0.06054 0.05592 -0.0765 0.0023 1.0000
15.000 1.6489 0.06510 0.06059 -0.0771 0.0023 1.0000
15.250 1.6399 0.06983 0.06544 -0.0778 0.0022 1.0000
15.500 1.6294 0.07482 0.07055 -0.0787 0.0022 1.0000
15.750 1.6182 0.08006 0.07592 -0.0798 0.0022 1.0000
16.000 1.6061 0.08551 0.08149 -0.0811 0.0022 1.0000
16.250 1.5931 0.09117 0.08726 -0.0825 0.0021 1.0000
16.500 1.5797 0.09699 0.09321 -0.0840 0.0021 1.0000
16.750 1.5667 0.10288 0.09921 -0.0857 0.0021 1.0000
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