GOE 417 AIRFOIL (goe417-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 417 AIRFOIL (goe417-il) Reynolds number: 1,000,000 Max Cl/Cd: 115.87 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe417-il-1000000-n5.txt Download as CSV file: xf-goe417-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 417 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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.1757 0.10960 0.10805 -0.0418 0.9897 0.0058
-10.750 -0.1674 0.10589 0.10433 -0.0437 0.9880 0.0059
-10.500 -0.2924 0.12023 0.11859 -0.0271 0.9997 0.0038
-10.250 -0.2777 0.11723 0.11560 -0.0299 0.9988 0.0058
-9.750 -0.2563 0.10917 0.10754 -0.0353 0.9943 0.0039
-9.500 -0.2451 0.10519 0.10356 -0.0381 0.9914 0.0040
-9.250 -0.2297 0.10304 0.10142 -0.0406 0.9888 0.0046
-9.000 -0.2181 0.09860 0.09698 -0.0440 0.9861 0.0043
-8.750 -0.2027 0.09679 0.09516 -0.0460 0.9821 0.0053
-8.500 -0.1884 0.09319 0.09157 -0.0494 0.9787 0.0049
-8.250 -0.1717 0.08966 0.08803 -0.0532 0.9758 0.0050
-8.000 -0.1548 0.08578 0.08415 -0.0575 0.9708 0.0047
-7.750 -0.1314 0.08104 0.07940 -0.0642 0.9663 0.0045
-7.500 -0.1091 0.07747 0.07581 -0.0695 0.9587 0.0048
-7.250 -0.0879 0.07325 0.07155 -0.0757 0.9490 0.0046
-7.000 -0.0679 0.06987 0.06813 -0.0804 0.9364 0.0048
-6.750 -0.0525 0.06671 0.06493 -0.0839 0.9229 0.0051
-6.500 -0.0385 0.06345 0.06161 -0.0870 0.9079 0.0053
-6.250 -0.0237 0.05985 0.05796 -0.0904 0.8938 0.0055
-6.000 -0.0073 0.05545 0.05348 -0.0947 0.8798 0.0060
-5.750 0.0122 0.05274 0.05070 -0.0976 0.8667 0.0062
-5.500 0.0332 0.05017 0.04806 -0.1004 0.8534 0.0064
-5.250 0.0558 0.04742 0.04521 -0.1033 0.8403 0.0068
-5.000 0.0804 0.04403 0.04171 -0.1068 0.8250 0.0074
-4.750 0.1116 0.03755 0.03503 -0.1134 0.8122 0.0084
-4.500 0.1377 0.03569 0.03307 -0.1151 0.7995 0.0088
-4.250 0.1642 0.03399 0.03127 -0.1166 0.7884 0.0093
-4.000 0.2001 0.02701 0.02396 -0.1218 0.7777 0.0114
-3.750 0.2266 0.02577 0.02260 -0.1224 0.7644 0.0118
-3.500 0.2531 0.02460 0.02130 -0.1229 0.7490 0.0123
-3.250 0.2860 0.01744 0.01356 -0.1251 0.7358 0.0155
-3.000 0.3115 0.01704 0.01302 -0.1249 0.7152 0.0158
-2.750 0.3365 0.01672 0.01253 -0.1245 0.6887 0.0163
-2.250 0.3886 0.01296 0.00794 -0.1236 0.6395 0.0197
-2.000 0.4144 0.01211 0.00677 -0.1233 0.6198 0.0202
-1.750 0.4402 0.01129 0.00574 -0.1230 0.6040 0.0206
-1.500 0.4663 0.01091 0.00521 -0.1227 0.5887 0.0209
-1.250 0.4926 0.01067 0.00487 -0.1224 0.5735 0.0213
-1.000 0.5187 0.01051 0.00458 -0.1220 0.5542 0.0218
-0.750 0.5443 0.01025 0.00414 -0.1215 0.5286 0.0223
-0.250 0.5953 0.00995 0.00347 -0.1205 0.4721 0.0235
0.000 0.6210 0.00982 0.00320 -0.1201 0.4499 0.0239
0.250 0.6468 0.00974 0.00299 -0.1196 0.4278 0.0243
0.500 0.6724 0.00968 0.00281 -0.1192 0.4067 0.0246
0.750 0.6978 0.00966 0.00266 -0.1187 0.3839 0.0248
1.500 0.7748 0.00968 0.00242 -0.1174 0.3348 0.0255
2.000 0.8264 0.00967 0.00228 -0.1166 0.3091 0.0256
2.250 0.8525 0.00967 0.00226 -0.1163 0.3018 0.0258
2.500 0.8789 0.00968 0.00224 -0.1160 0.2961 0.0260
2.750 0.9049 0.00974 0.00228 -0.1156 0.2899 0.0263
3.250 0.9574 0.00977 0.00229 -0.1150 0.2787 0.0289
3.500 0.9834 0.00986 0.00236 -0.1147 0.2729 0.0301
3.750 1.0095 0.00995 0.00245 -0.1144 0.2668 0.0310
4.000 1.0352 0.01008 0.00255 -0.1140 0.2597 0.0318
4.250 1.0612 0.01018 0.00266 -0.1136 0.2531 0.0333
4.500 1.0863 0.01035 0.00279 -0.1132 0.2413 0.0345
4.750 1.1110 0.01058 0.00296 -0.1127 0.2247 0.0353
5.000 1.1357 0.01080 0.00314 -0.1122 0.2116 0.0442
5.500 1.1842 0.01022 0.00394 -0.1117 0.1704 1.0000
5.750 1.2059 0.01074 0.00429 -0.1107 0.1441 1.0000
6.000 1.2291 0.01110 0.00458 -0.1100 0.1305 1.0000
6.250 1.2527 0.01143 0.00485 -0.1094 0.1207 1.0000
6.500 1.2764 0.01172 0.00513 -0.1087 0.1123 1.0000
6.750 1.2994 0.01208 0.00543 -0.1080 0.1027 1.0000
7.000 1.3167 0.01300 0.00607 -0.1064 0.0566 1.0000
7.250 1.3360 0.01370 0.00668 -0.1051 0.0344 1.0000
7.500 1.3551 0.01441 0.00730 -0.1038 0.0147 1.0000
7.750 1.3773 0.01478 0.00770 -0.1029 0.0114 1.0000
8.000 1.3986 0.01523 0.00816 -0.1019 0.0093 1.0000
8.250 1.4195 0.01568 0.00864 -0.1009 0.0079 1.0000
8.500 1.4406 0.01609 0.00909 -0.0998 0.0071 1.0000
8.750 1.4607 0.01656 0.00961 -0.0987 0.0064 1.0000
9.000 1.4793 0.01715 0.01023 -0.0973 0.0055 1.0000
9.250 1.4988 0.01761 0.01074 -0.0961 0.0052 1.0000
9.500 1.5174 0.01812 0.01130 -0.0947 0.0048 1.0000
9.750 1.5352 0.01863 0.01185 -0.0932 0.0043 1.0000
10.000 1.5504 0.01921 0.01246 -0.0913 0.0040 1.0000
10.250 1.5626 0.01991 0.01324 -0.0888 0.0037 1.0000
10.500 1.5742 0.02064 0.01405 -0.0864 0.0035 1.0000
10.750 1.5867 0.02132 0.01480 -0.0841 0.0034 1.0000
11.000 1.5983 0.02206 0.01561 -0.0818 0.0032 1.0000
11.250 1.6081 0.02291 0.01655 -0.0794 0.0031 1.0000
11.500 1.6180 0.02378 0.01750 -0.0771 0.0029 1.0000
11.750 1.6270 0.02474 0.01853 -0.0748 0.0028 1.0000
12.000 1.6347 0.02581 0.01969 -0.0725 0.0027 1.0000
12.250 1.6422 0.02692 0.02088 -0.0703 0.0026 1.0000
12.500 1.6488 0.02815 0.02219 -0.0682 0.0025 1.0000
12.750 1.6529 0.02962 0.02374 -0.0660 0.0023 1.0000
13.000 1.6517 0.03160 0.02583 -0.0636 0.0022 1.0000
13.250 1.6508 0.03367 0.02802 -0.0615 0.0022 1.0000
13.500 1.6517 0.03570 0.03016 -0.0598 0.0021 1.0000
13.750 1.6533 0.03778 0.03234 -0.0584 0.0021 1.0000
14.000 1.6499 0.04049 0.03518 -0.0571 0.0020 1.0000
14.250 1.6493 0.04307 0.03787 -0.0563 0.0020 1.0000
14.500 1.6422 0.04658 0.04152 -0.0557 0.0020 1.0000
14.750 1.6386 0.04990 0.04496 -0.0555 0.0019 1.0000
15.000 1.6299 0.05415 0.04935 -0.0558 0.0019 1.0000
15.250 1.6195 0.05890 0.05424 -0.0567 0.0018 1.0000
15.500 1.6091 0.06393 0.05941 -0.0579 0.0018 1.0000
15.750 1.6007 0.06889 0.06449 -0.0593 0.0018 1.0000
16.000 1.5863 0.07502 0.07076 -0.0614 0.0018 1.0000
16.250 1.5713 0.08153 0.07742 -0.0638 0.0018 1.0000
16.500 1.5570 0.08812 0.08414 -0.0664 0.0018 1.0000
16.750 1.5425 0.09487 0.09103 -0.0693 0.0017 1.0000
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