GOE 265 AIRFOIL (goe265-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 265 AIRFOIL (goe265-il) Reynolds number: 500,000 Max Cl/Cd: 109.06 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe265-il-500000-n5.txt Download as CSV file: xf-goe265-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 265 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2384 0.10308 0.10055 -0.0218 0.8472 0.0098
-8.500 -0.2272 0.09616 0.09345 -0.0247 0.7985 0.0100
-7.500 -0.1904 0.08535 0.08235 -0.0312 0.7304 0.0108
-7.250 -0.1763 0.08284 0.07978 -0.0336 0.7195 0.0112
-7.000 -0.1613 0.07968 0.07658 -0.0370 0.7098 0.0118
-6.750 -0.1451 0.07534 0.07220 -0.0421 0.7009 0.0124
-6.500 -0.1260 0.06894 0.06573 -0.0501 0.6933 0.0131
-6.250 -0.1042 0.06662 0.06336 -0.0534 0.6840 0.0134
-6.000 -0.0811 0.06414 0.06083 -0.0570 0.6753 0.0138
-5.750 -0.0563 0.06128 0.05791 -0.0612 0.6654 0.0147
-5.500 -0.0221 0.05411 0.05061 -0.0719 0.6569 0.0166
-5.250 0.0048 0.05218 0.04860 -0.0749 0.6443 0.0170
-4.250 0.1895 0.01503 0.00920 -0.1193 0.6108 0.0301
-4.000 0.2183 0.01377 0.00764 -0.1198 0.6014 0.0311
-3.750 0.2466 0.01342 0.00718 -0.1198 0.5924 0.0320
-3.500 0.2750 0.01302 0.00662 -0.1198 0.5834 0.0328
-3.250 0.3036 0.01253 0.00596 -0.1199 0.5753 0.0336
-2.750 0.3605 0.01175 0.00484 -0.1198 0.5584 0.0354
-2.250 0.4172 0.01120 0.00402 -0.1196 0.5434 0.0369
-2.000 0.4455 0.01090 0.00362 -0.1195 0.5356 0.0381
-1.750 0.4739 0.01072 0.00339 -0.1194 0.5281 0.0393
-1.500 0.5021 0.01060 0.00319 -0.1193 0.5205 0.0406
-1.250 0.5304 0.01048 0.00301 -0.1191 0.5140 0.0421
-1.000 0.5586 0.01039 0.00285 -0.1190 0.5066 0.0438
-0.750 0.5867 0.01029 0.00271 -0.1188 0.4993 0.0463
-0.500 0.6149 0.01024 0.00264 -0.1187 0.4912 0.0494
-0.250 0.6429 0.01021 0.00255 -0.1185 0.4837 0.0527
0.000 0.6709 0.01018 0.00251 -0.1184 0.4743 0.0569
0.250 0.6988 0.01021 0.00250 -0.1182 0.4635 0.0617
0.500 0.7265 0.01025 0.00247 -0.1180 0.4526 0.0659
0.750 0.7543 0.01031 0.00251 -0.1179 0.4414 0.0711
1.000 0.7821 0.01038 0.00254 -0.1177 0.4317 0.0757
1.250 0.8097 0.01043 0.00256 -0.1175 0.4218 0.0800
1.500 0.8373 0.01052 0.00262 -0.1174 0.4113 0.0847
1.750 0.8648 0.01062 0.00268 -0.1172 0.4010 0.0893
2.000 0.8921 0.01071 0.00272 -0.1170 0.3903 0.0931
2.250 0.9194 0.01082 0.00281 -0.1168 0.3791 0.0975
2.500 0.9466 0.01094 0.00289 -0.1166 0.3686 0.1018
2.750 0.9736 0.01109 0.00298 -0.1164 0.3578 0.1049
3.250 1.0276 0.01135 0.00322 -0.1161 0.3391 0.1149
3.750 1.0815 0.01163 0.00348 -0.1157 0.3249 0.1259
4.000 1.1083 0.01178 0.00364 -0.1155 0.3188 0.1329
4.250 1.1350 0.01193 0.00380 -0.1153 0.3134 0.1418
4.500 1.1619 0.01207 0.00397 -0.1151 0.3077 0.1546
4.750 1.1883 0.01223 0.00417 -0.1149 0.3019 0.1734
5.000 1.2150 0.01235 0.00439 -0.1147 0.2973 0.2208
5.500 1.2651 0.01165 0.00487 -0.1139 0.2874 1.0000
5.750 1.2912 0.01188 0.00508 -0.1136 0.2821 1.0000
6.000 1.3174 0.01208 0.00529 -0.1133 0.2773 1.0000
6.250 1.3433 0.01232 0.00552 -0.1130 0.2723 1.0000
6.500 1.3689 0.01257 0.00577 -0.1127 0.2676 1.0000
6.750 1.3948 0.01279 0.00601 -0.1124 0.2620 1.0000
7.000 1.4200 0.01307 0.00628 -0.1121 0.2557 1.0000
7.250 1.4452 0.01334 0.00656 -0.1117 0.2496 1.0000
7.500 1.4701 0.01362 0.00685 -0.1113 0.2423 1.0000
7.750 1.4947 0.01394 0.00717 -0.1109 0.2352 1.0000
8.000 1.5189 0.01427 0.00750 -0.1105 0.2261 1.0000
8.250 1.5421 0.01469 0.00789 -0.1099 0.2124 1.0000
8.500 1.5618 0.01545 0.00847 -0.1089 0.1820 1.0000
9.000 1.5956 0.01741 0.01009 -0.1063 0.1293 1.0000
9.250 1.6159 0.01799 0.01068 -0.1054 0.1232 1.0000
9.500 1.6352 0.01862 0.01131 -0.1044 0.1178 1.0000
9.750 1.6535 0.01930 0.01200 -0.1032 0.1117 1.0000
10.000 1.6726 0.01985 0.01261 -0.1021 0.1069 1.0000
10.250 1.6893 0.02056 0.01333 -0.1008 0.1017 1.0000
10.500 1.7055 0.02126 0.01406 -0.0993 0.0971 1.0000
10.750 1.7221 0.02184 0.01470 -0.0979 0.0914 1.0000
11.000 1.7325 0.02269 0.01554 -0.0957 0.0830 1.0000
11.250 1.7330 0.02422 0.01692 -0.0925 0.0608 1.0000
11.500 1.7250 0.02655 0.01913 -0.0891 0.0401 1.0000
11.750 1.7086 0.02994 0.02244 -0.0859 0.0189 1.0000
12.000 1.7082 0.03229 0.02485 -0.0844 0.0153 1.0000
12.250 1.7109 0.03449 0.02714 -0.0834 0.0137 1.0000
12.500 1.7117 0.03703 0.02978 -0.0826 0.0125 1.0000
12.750 1.7116 0.03978 0.03264 -0.0820 0.0116 1.0000
13.000 1.7130 0.04244 0.03541 -0.0816 0.0110 1.0000
13.250 1.7122 0.04541 0.03849 -0.0813 0.0105 1.0000
13.500 1.7095 0.04865 0.04186 -0.0810 0.0100 1.0000
13.750 1.7048 0.05220 0.04552 -0.0809 0.0096 1.0000
14.000 1.6980 0.05605 0.04948 -0.0808 0.0092 1.0000
14.250 1.6889 0.06029 0.05384 -0.0810 0.0089 1.0000
14.500 1.6806 0.06450 0.05817 -0.0812 0.0087 1.0000
14.750 1.6735 0.06867 0.06246 -0.0816 0.0084 1.0000
15.000 1.6656 0.07306 0.06697 -0.0821 0.0082 1.0000
15.250 1.6569 0.07764 0.07168 -0.0828 0.0080 1.0000
15.500 1.6473 0.08242 0.07658 -0.0836 0.0078 1.0000
15.750 1.6374 0.08736 0.08164 -0.0845 0.0076 1.0000
16.000 1.6272 0.09242 0.08680 -0.0856 0.0074 1.0000
16.250 1.6160 0.09766 0.09216 -0.0868 0.0072 1.0000
16.500 1.6047 0.10304 0.09765 -0.0881 0.0071 1.0000
16.750 1.5929 0.10857 0.10330 -0.0896 0.0069 1.0000
17.000 1.5810 0.11418 0.10902 -0.0913 0.0068 1.0000
17.250 1.5687 0.11991 0.11486 -0.0931 0.0067 1.0000
17.500 1.5564 0.12575 0.12081 -0.0951 0.0066 1.0000
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Polar data table (+)
Polar graphs
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