GOE 413 AIRFOIL (goe413-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 413 AIRFOIL (goe413-il) Reynolds number: 50,000 Max Cl/Cd: 23.9 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe413-il-50000-n5.txt Download as CSV file: xf-goe413-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 413 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.2591 0.11855 0.11093 -0.0478 1.0000 0.1008
-10.250 -0.2600 0.11628 0.10875 -0.0474 1.0000 0.1005
-10.000 -0.2663 0.11462 0.10720 -0.0459 1.0000 0.1001
-9.750 -0.2767 0.11335 0.10603 -0.0438 1.0000 0.0996
-9.500 -0.2616 0.10893 0.10159 -0.0482 0.9905 0.0987
-9.250 -0.2479 0.10425 0.09689 -0.0531 0.9810 0.0976
-9.000 -0.2365 0.09932 0.09193 -0.0581 0.9713 0.0967
-8.750 -0.2259 0.09416 0.08674 -0.0637 0.9623 0.0962
-8.500 -0.2174 0.08919 0.08176 -0.0689 0.9515 0.0966
-8.250 -0.2127 0.08402 0.07657 -0.0740 0.9397 0.0969
-8.000 -0.2115 0.07820 0.07072 -0.0798 0.9279 0.0970
-7.750 -0.2247 0.07028 0.06275 -0.0873 0.9135 0.0964
-7.500 -0.2757 0.05418 0.04608 -0.1049 0.8943 0.0948
-7.250 -0.2772 0.04908 0.04055 -0.1085 0.8803 0.0951
-7.000 -0.2623 0.04551 0.03658 -0.1112 0.8705 0.0959
-6.750 -0.2454 0.04296 0.03371 -0.1125 0.8597 0.0972
-6.500 -0.2235 0.04057 0.03091 -0.1140 0.8512 0.0993
-6.250 -0.2035 0.03873 0.02873 -0.1144 0.8408 0.1012
-6.000 -0.1744 0.03765 0.02760 -0.1152 0.8345 0.1032
-5.750 -0.1558 0.03678 0.02662 -0.1145 0.8231 0.1050
-5.500 -0.1281 0.03553 0.02516 -0.1150 0.8163 0.1072
-5.250 -0.1060 0.03459 0.02402 -0.1147 0.8067 0.1095
-5.000 -0.0799 0.03380 0.02316 -0.1148 0.7990 0.1125
-4.750 -0.0522 0.03314 0.02243 -0.1150 0.7926 0.1168
-4.500 -0.0305 0.03260 0.02176 -0.1145 0.7828 0.1217
-4.250 -0.0019 0.03201 0.02118 -0.1147 0.7768 0.1274
-4.000 0.0211 0.03158 0.02068 -0.1143 0.7683 0.1344
-3.750 0.0469 0.03111 0.02021 -0.1142 0.7609 0.1441
-3.500 0.0772 0.03049 0.01958 -0.1146 0.7560 0.1616
-3.250 0.0980 0.03046 0.01964 -0.1141 0.7465 0.1817
-3.000 0.1260 0.03019 0.01931 -0.1142 0.7403 0.2095
-2.750 0.1548 0.03001 0.01914 -0.1143 0.7351 0.2332
-2.500 0.1758 0.03033 0.01951 -0.1138 0.7260 0.2563
-2.250 0.2045 0.03032 0.01947 -0.1139 0.7206 0.2827
-2.000 0.2303 0.03043 0.01956 -0.1136 0.7142 0.3024
-1.750 0.2534 0.03066 0.01980 -0.1131 0.7064 0.3195
-1.500 0.2827 0.03054 0.01963 -0.1131 0.7014 0.3387
-1.250 0.3075 0.03070 0.01980 -0.1127 0.6947 0.3583
-1.000 0.3311 0.03092 0.02004 -0.1122 0.6873 0.3789
-0.750 0.3608 0.03073 0.01984 -0.1121 0.6826 0.4008
-0.500 0.3856 0.03084 0.01998 -0.1117 0.6760 0.4202
-0.250 0.4088 0.03105 0.02023 -0.1111 0.6685 0.4396
0.000 0.4385 0.03083 0.02003 -0.1109 0.6637 0.4637
0.250 0.4636 0.03095 0.02020 -0.1104 0.6574 0.4895
0.500 0.4849 0.03133 0.02066 -0.1096 0.6494 0.5178
0.750 0.5140 0.03111 0.02049 -0.1091 0.6445 0.5537
1.000 0.5392 0.03113 0.02060 -0.1083 0.6387 0.5918
1.250 0.5557 0.03166 0.02131 -0.1068 0.6300 0.6301
1.500 0.5799 0.03137 0.02121 -0.1051 0.6251 0.6816
1.750 0.6040 0.03085 0.02086 -0.1027 0.6214 0.7540
2.000 0.6065 0.03187 0.02217 -0.0993 0.6105 0.8439
2.250 0.6404 0.03166 0.02186 -0.0998 0.6051 1.0000
2.500 0.6784 0.03144 0.02138 -0.1008 0.6015 1.0000
2.750 0.6866 0.03317 0.02310 -0.0999 0.5897 1.0000
3.000 0.7189 0.03323 0.02299 -0.1002 0.5847 1.0000
3.250 0.7492 0.03343 0.02304 -0.1003 0.5794 1.0000
3.500 0.7590 0.03501 0.02462 -0.0992 0.5686 1.0000
3.750 0.7918 0.03498 0.02446 -0.0994 0.5639 1.0000
4.000 0.8063 0.03624 0.02571 -0.0985 0.5551 1.0000
4.500 0.8612 0.03685 0.02616 -0.0980 0.5431 1.0000
4.750 0.8618 0.03909 0.02846 -0.0963 0.5317 1.0000
5.000 0.8900 0.03928 0.02859 -0.0960 0.5260 1.0000
5.250 0.9277 0.03882 0.02804 -0.0963 0.5225 1.0000
5.500 0.9154 0.04198 0.03130 -0.0939 0.5092 1.0000
5.750 0.9497 0.04169 0.03095 -0.0938 0.5051 1.0000
6.250 0.9640 0.04506 0.03437 -0.0909 0.4877 1.0000
6.500 1.0037 0.04432 0.03358 -0.0910 0.4848 1.0000
6.750 0.9749 0.04916 0.03853 -0.0887 0.4702 1.0000
7.000 1.0111 0.04845 0.03779 -0.0882 0.4672 1.0000
7.500 1.0153 0.05342 0.04285 -0.0862 0.4495 1.0000
8.000 1.0173 0.05907 0.04859 -0.0848 0.4319 1.0000
8.250 1.0521 0.05817 0.04770 -0.0840 0.4298 1.0000
8.750 1.0354 0.06638 0.05603 -0.0831 0.4101 1.0000
9.250 1.0423 0.07212 0.06188 -0.0824 0.3951 1.0000
10.250 1.0336 0.08663 0.07662 -0.0820 0.3619 1.0000
10.500 1.0642 0.08524 0.07525 -0.0804 0.3576 1.0000
11.000 1.0841 0.08819 0.07831 -0.0790 0.3420 1.0000
11.500 1.0945 0.09247 0.08270 -0.0781 0.3250 1.0000
12.000 1.1015 0.09742 0.08779 -0.0776 0.3080 1.0000
12.500 1.1139 0.10123 0.09172 -0.0768 0.2908 1.0000
13.000 1.1314 0.10403 0.09464 -0.0759 0.2733 1.0000
13.500 1.1448 0.10783 0.09860 -0.0756 0.2559 1.0000
13.750 1.1252 0.11454 0.10542 -0.0776 0.2425 1.0000
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Polar data table (+)
Polar graphs
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