GOE 359 AIRFOIL (goe359-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 359 AIRFOIL (goe359-il) Reynolds number: 1,000,000 Max Cl/Cd: 103.77 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe359-il-1000000-n5.txt Download as CSV file: xf-goe359-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 359 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.2288 0.09167 0.08958 -0.0421 0.8350 0.0039
-8.250 -0.2231 0.08824 0.08610 -0.0438 0.8192 0.0039
-8.000 -0.2176 0.08470 0.08251 -0.0458 0.8054 0.0040
-7.750 -0.2096 0.08172 0.07949 -0.0478 0.7925 0.0041
-7.500 -0.2003 0.07881 0.07654 -0.0503 0.7807 0.0042
-7.250 -0.1866 0.07556 0.07326 -0.0539 0.7693 0.0043
-7.000 -0.1711 0.07202 0.06967 -0.0582 0.7580 0.0045
-6.750 -0.1536 0.06802 0.06562 -0.0633 0.7464 0.0047
-6.500 -0.1333 0.06292 0.06046 -0.0701 0.7346 0.0051
-6.250 -0.1039 0.05193 0.04936 -0.0852 0.7251 0.0061
-6.000 -0.0770 0.04863 0.04596 -0.0899 0.7128 0.0065
-5.750 -0.0481 0.04473 0.04194 -0.0951 0.7011 0.0069
-5.500 -0.0020 0.02861 0.02525 -0.1114 0.6937 0.0090
-5.250 0.0264 0.02528 0.02172 -0.1135 0.6829 0.0100
-5.000 0.0536 0.01523 0.01068 -0.1168 0.6747 0.0127
-4.750 0.0810 0.01534 0.01076 -0.1167 0.6631 0.0138
-4.500 0.1067 0.01224 0.00706 -0.1170 0.6531 0.0177
-4.250 0.1342 0.01215 0.00686 -0.1169 0.6416 0.0181
-3.750 0.1895 0.01235 0.00695 -0.1167 0.6200 0.0194
-3.500 0.2171 0.01254 0.00710 -0.1166 0.6109 0.0200
-3.000 0.2720 0.01235 0.00672 -0.1165 0.5884 0.0217
-2.750 0.2994 0.01198 0.00620 -0.1164 0.5754 0.0225
-2.500 0.3269 0.01152 0.00559 -0.1163 0.5632 0.0232
-2.250 0.3544 0.01101 0.00491 -0.1162 0.5524 0.0236
-2.000 0.3819 0.01068 0.00446 -0.1161 0.5418 0.0243
-1.750 0.4095 0.01029 0.00395 -0.1160 0.5311 0.0248
-1.500 0.4370 0.01003 0.00359 -0.1159 0.5200 0.0253
-1.250 0.4645 0.00989 0.00337 -0.1158 0.5091 0.0259
-1.000 0.4920 0.00984 0.00324 -0.1157 0.4982 0.0264
-0.750 0.5196 0.00982 0.00317 -0.1156 0.4878 0.0267
-0.500 0.5469 0.00957 0.00283 -0.1155 0.4773 0.0274
-0.250 0.5740 0.00921 0.00239 -0.1154 0.4671 0.0284
0.000 0.6015 0.00906 0.00220 -0.1153 0.4576 0.0290
0.250 0.6287 0.00899 0.00207 -0.1152 0.4457 0.0293
0.500 0.6558 0.00897 0.00198 -0.1151 0.4316 0.0296
0.750 0.6830 0.00895 0.00190 -0.1149 0.4218 0.0298
1.000 0.7105 0.00893 0.00185 -0.1149 0.4123 0.0303
1.250 0.7377 0.00895 0.00182 -0.1147 0.4010 0.0308
1.500 0.7648 0.00898 0.00179 -0.1146 0.3902 0.0308
1.750 0.7921 0.00901 0.00178 -0.1145 0.3806 0.0308
2.000 0.8194 0.00905 0.00178 -0.1144 0.3706 0.0308
2.250 0.8462 0.00915 0.00181 -0.1143 0.3553 0.0310
2.500 0.8721 0.00934 0.00188 -0.1140 0.3292 0.0314
2.750 0.8965 0.00973 0.00204 -0.1135 0.2846 0.0323
3.000 0.9211 0.01010 0.00224 -0.1130 0.2504 0.0345
3.250 0.9467 0.01034 0.00241 -0.1127 0.2325 0.0391
3.750 0.9980 0.01073 0.00283 -0.1122 0.1986 0.1500
4.000 1.0201 0.00983 0.00327 -0.1118 0.1788 0.8584
4.500 1.0606 0.01130 0.00429 -0.1094 0.0572 1.0000
4.750 1.0859 0.01158 0.00453 -0.1090 0.0505 1.0000
5.000 1.1113 0.01184 0.00476 -0.1087 0.0445 1.0000
5.250 1.1343 0.01235 0.00516 -0.1080 0.0204 1.0000
5.500 1.1591 0.01266 0.00544 -0.1076 0.0137 1.0000
5.750 1.1841 0.01293 0.00574 -0.1072 0.0118 1.0000
6.000 1.2087 0.01325 0.00608 -0.1067 0.0101 1.0000
6.250 1.2328 0.01359 0.00648 -0.1062 0.0086 1.0000
6.500 1.2571 0.01391 0.00680 -0.1057 0.0076 1.0000
6.750 1.2808 0.01426 0.00718 -0.1051 0.0068 1.0000
7.000 1.3037 0.01470 0.00766 -0.1044 0.0060 1.0000
7.250 1.3268 0.01508 0.00809 -0.1038 0.0056 1.0000
7.500 1.3496 0.01548 0.00851 -0.1031 0.0051 1.0000
7.750 1.3720 0.01589 0.00893 -0.1024 0.0046 1.0000
8.000 1.3928 0.01643 0.00951 -0.1014 0.0041 1.0000
8.250 1.4131 0.01700 0.01014 -0.1003 0.0039 1.0000
8.500 1.4333 0.01755 0.01074 -0.0992 0.0037 1.0000
8.750 1.4523 0.01815 0.01142 -0.0980 0.0035 1.0000
9.000 1.4706 0.01878 0.01211 -0.0967 0.0032 1.0000
9.250 1.4881 0.01944 0.01282 -0.0953 0.0031 1.0000
9.500 1.5045 0.02012 0.01355 -0.0937 0.0029 1.0000
9.750 1.5187 0.02082 0.01431 -0.0918 0.0028 1.0000
10.000 1.5273 0.02177 0.01533 -0.0890 0.0026 1.0000
10.250 1.5350 0.02279 0.01644 -0.0862 0.0025 1.0000
10.500 1.5442 0.02374 0.01747 -0.0838 0.0024 1.0000
10.750 1.5514 0.02488 0.01871 -0.0813 0.0023 1.0000
11.000 1.5564 0.02626 0.02021 -0.0790 0.0022 1.0000
11.250 1.5595 0.02792 0.02197 -0.0767 0.0022 1.0000
11.500 1.5617 0.02979 0.02395 -0.0748 0.0021 1.0000
11.750 1.5634 0.03188 0.02615 -0.0732 0.0020 1.0000
12.000 1.5639 0.03421 0.02858 -0.0719 0.0020 1.0000
12.250 1.5635 0.03677 0.03125 -0.0708 0.0019 1.0000
12.500 1.5626 0.03950 0.03408 -0.0699 0.0019 1.0000
12.750 1.5610 0.04242 0.03710 -0.0693 0.0018 1.0000
13.000 1.5592 0.04549 0.04027 -0.0688 0.0018 1.0000
13.250 1.5556 0.04881 0.04371 -0.0685 0.0018 1.0000
13.500 1.5523 0.05222 0.04721 -0.0684 0.0017 1.0000
13.750 1.5483 0.05578 0.05088 -0.0685 0.0017 1.0000
14.000 1.5441 0.05942 0.05462 -0.0686 0.0017 1.0000
14.250 1.5367 0.06361 0.05891 -0.0689 0.0017 1.0000
14.500 1.5307 0.06773 0.06313 -0.0694 0.0016 1.0000
14.750 1.5223 0.07225 0.06776 -0.0700 0.0016 1.0000
15.000 1.5162 0.07657 0.07217 -0.0708 0.0016 1.0000
15.250 1.5069 0.08140 0.07711 -0.0717 0.0016 1.0000
15.500 1.4969 0.08643 0.08227 -0.0727 0.0015 1.0000
15.750 1.4863 0.09155 0.08750 -0.0738 0.0015 1.0000
16.000 1.4741 0.09697 0.09303 -0.0750 0.0015 1.0000
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Polar data table (+)
Polar graphs
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