GOE 478 AIRFOIL (goe478-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 478 AIRFOIL (goe478-il) Reynolds number: 1,000,000 Max Cl/Cd: 114.78 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe478-il-1000000-n5.txt Download as CSV file: xf-goe478-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 478 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
------ -------- --------- --------- -------- -------- --------
-14.750 -0.8171 0.06268 0.06001 -0.0817 1.0000 0.0233
-14.500 -0.9279 0.03418 0.03087 -0.1127 0.9958 0.0232
-14.250 -0.9290 0.03115 0.02768 -0.1148 0.9892 0.0232
-13.750 -0.9157 0.02749 0.02374 -0.1144 0.9725 0.0233
-13.500 -0.8983 0.02596 0.02208 -0.1149 0.9639 0.0234
-13.000 -0.8397 0.02332 0.01918 -0.1194 0.9485 0.0235
-12.750 -0.8015 0.02196 0.01768 -0.1233 0.9407 0.0236
-12.500 -0.7658 0.02058 0.01614 -0.1267 0.9272 0.0238
-12.250 -0.7377 0.01956 0.01497 -0.1280 0.9087 0.0240
-12.000 -0.7169 0.01889 0.01416 -0.1274 0.8900 0.0241
-11.750 -0.6985 0.01833 0.01348 -0.1261 0.8727 0.0243
-11.500 -0.6802 0.01782 0.01285 -0.1247 0.8566 0.0244
-11.250 -0.6613 0.01735 0.01227 -0.1233 0.8416 0.0245
-11.000 -0.6420 0.01690 0.01171 -0.1219 0.8276 0.0246
-10.750 -0.6216 0.01653 0.01124 -0.1206 0.8143 0.0247
-10.500 -0.6012 0.01611 0.01073 -0.1194 0.8017 0.0249
-10.250 -0.5799 0.01572 0.01025 -0.1183 0.7914 0.0250
-10.000 -0.5587 0.01535 0.00978 -0.1171 0.7808 0.0252
-9.750 -0.5364 0.01498 0.00933 -0.1161 0.7715 0.0253
-9.250 -0.4907 0.01429 0.00848 -0.1143 0.7566 0.0257
-9.000 -0.4670 0.01397 0.00810 -0.1135 0.7510 0.0260
-8.500 -0.4189 0.01337 0.00736 -0.1120 0.7413 0.0264
-8.250 -0.3941 0.01306 0.00700 -0.1114 0.7378 0.0266
-8.000 -0.3693 0.01276 0.00665 -0.1107 0.7342 0.0267
-7.750 -0.3444 0.01248 0.00632 -0.1101 0.7306 0.0269
-7.500 -0.3193 0.01223 0.00601 -0.1095 0.7272 0.0270
-7.250 -0.2940 0.01198 0.00571 -0.1089 0.7240 0.0271
-7.000 -0.2691 0.01161 0.00532 -0.1083 0.7214 0.0275
-6.750 -0.2436 0.01132 0.00501 -0.1077 0.7184 0.0277
-6.500 -0.2178 0.01108 0.00475 -0.1072 0.7154 0.0280
-6.250 -0.1919 0.01086 0.00450 -0.1067 0.7120 0.0283
-6.000 -0.1659 0.01068 0.00428 -0.1062 0.7088 0.0287
-5.500 -0.1130 0.01031 0.00388 -0.1053 0.7036 0.0293
-5.250 -0.0863 0.01012 0.00368 -0.1049 0.7005 0.0297
-5.000 -0.0596 0.00996 0.00350 -0.1046 0.6971 0.0301
-4.750 -0.0329 0.00980 0.00332 -0.1041 0.6939 0.0305
-4.500 -0.0063 0.00966 0.00316 -0.1037 0.6909 0.0308
-4.250 0.0199 0.00952 0.00298 -0.1032 0.6870 0.0313
-4.000 0.0468 0.00934 0.00282 -0.1029 0.6833 0.0320
-3.750 0.0737 0.00920 0.00269 -0.1025 0.6789 0.0328
-3.500 0.1005 0.00908 0.00256 -0.1021 0.6740 0.0336
-3.250 0.1270 0.00899 0.00244 -0.1016 0.6696 0.0344
-3.000 0.1541 0.00888 0.00233 -0.1013 0.6655 0.0351
-2.750 0.1811 0.00875 0.00221 -0.1009 0.6603 0.0363
-2.500 0.2075 0.00866 0.00211 -0.1004 0.6533 0.0376
-2.250 0.2341 0.00858 0.00202 -0.0999 0.6456 0.0391
-2.000 0.2598 0.00851 0.00193 -0.0993 0.6335 0.0410
-1.750 0.2853 0.00846 0.00185 -0.0986 0.6165 0.0434
-1.500 0.3084 0.00850 0.00179 -0.0975 0.5840 0.0463
-1.000 0.3538 0.00868 0.00176 -0.0951 0.5301 0.0557
-0.500 0.4029 0.00865 0.00177 -0.0935 0.5057 0.0895
-0.250 0.4280 0.00869 0.00179 -0.0928 0.4965 0.0988
0.000 0.4540 0.00868 0.00179 -0.0922 0.4902 0.1054
0.250 0.4800 0.00869 0.00180 -0.0917 0.4838 0.1112
0.500 0.5051 0.00871 0.00183 -0.0910 0.4771 0.1204
0.750 0.5311 0.00869 0.00184 -0.0905 0.4718 0.1316
1.000 0.5565 0.00865 0.00188 -0.0899 0.4663 0.1607
1.250 0.5816 0.00865 0.00194 -0.0892 0.4609 0.1883
1.500 0.6070 0.00867 0.00199 -0.0886 0.4552 0.2042
1.750 0.6326 0.00869 0.00203 -0.0880 0.4478 0.2160
2.000 0.6566 0.00876 0.00209 -0.0871 0.4382 0.2308
2.250 0.6817 0.00878 0.00214 -0.0864 0.4295 0.2485
2.500 0.7052 0.00878 0.00220 -0.0855 0.4218 0.2870
2.750 0.7256 0.00840 0.00230 -0.0841 0.4169 0.4737
3.000 0.7458 0.00816 0.00240 -0.0825 0.4101 0.6081
3.250 0.7609 0.00789 0.00252 -0.0798 0.4027 0.7603
3.500 0.8192 0.00771 0.00281 -0.0862 0.3921 0.9625
3.750 0.8694 0.00792 0.00296 -0.0911 0.3838 0.9790
4.000 0.9063 0.00807 0.00308 -0.0931 0.3759 0.9878
4.250 0.9373 0.00827 0.00321 -0.0938 0.3658 0.9953
4.500 0.9745 0.00849 0.00337 -0.0959 0.3524 0.9996
4.750 0.9961 0.00869 0.00349 -0.0946 0.3377 1.0000
5.000 1.0136 0.00891 0.00364 -0.0925 0.3222 1.0000
5.250 1.0312 0.00913 0.00379 -0.0903 0.3078 1.0000
5.500 1.0471 0.00942 0.00398 -0.0879 0.2891 1.0000
5.750 1.0604 0.00982 0.00423 -0.0850 0.2636 1.0000
6.000 1.0716 0.01028 0.00453 -0.0818 0.2365 1.0000
6.250 1.0836 0.01062 0.00478 -0.0786 0.2196 1.0000
6.500 1.0962 0.01095 0.00503 -0.0756 0.2044 1.0000
6.750 1.1107 0.01126 0.00528 -0.0730 0.1921 1.0000
7.000 1.1266 0.01156 0.00553 -0.0708 0.1822 1.0000
7.250 1.1422 0.01189 0.00581 -0.0685 0.1719 1.0000
7.500 1.1584 0.01222 0.00610 -0.0664 0.1624 1.0000
7.750 1.1753 0.01256 0.00639 -0.0644 0.1540 1.0000
8.000 1.1907 0.01295 0.00673 -0.0623 0.1444 1.0000
8.250 1.2076 0.01331 0.00706 -0.0605 0.1364 1.0000
8.500 1.2239 0.01372 0.00743 -0.0586 0.1290 1.0000
8.750 1.2404 0.01413 0.00781 -0.0568 0.1221 1.0000
9.000 1.2568 0.01455 0.00821 -0.0550 0.1160 1.0000
9.250 1.2730 0.01500 0.00864 -0.0533 0.1099 1.0000
9.500 1.2888 0.01549 0.00910 -0.0516 0.1039 1.0000
9.750 1.3038 0.01604 0.00962 -0.0498 0.0973 1.0000
10.000 1.3196 0.01656 0.01014 -0.0482 0.0923 1.0000
10.250 1.3330 0.01724 0.01077 -0.0464 0.0848 1.0000
10.500 1.3475 0.01787 0.01139 -0.0448 0.0787 1.0000
10.750 1.3612 0.01858 0.01208 -0.0432 0.0736 1.0000
11.000 1.3750 0.01930 0.01279 -0.0417 0.0692 1.0000
11.250 1.3884 0.02008 0.01357 -0.0401 0.0655 1.0000
11.500 1.4027 0.02082 0.01431 -0.0388 0.0632 1.0000
11.750 1.4156 0.02166 0.01517 -0.0374 0.0609 1.0000
12.000 1.4287 0.02251 0.01603 -0.0360 0.0591 1.0000
12.250 1.4425 0.02334 0.01689 -0.0348 0.0577 1.0000
12.500 1.4553 0.02427 0.01785 -0.0336 0.0564 1.0000
12.750 1.4672 0.02527 0.01888 -0.0324 0.0552 1.0000
13.000 1.4779 0.02637 0.02000 -0.0311 0.0537 1.0000
13.250 1.4887 0.02751 0.02117 -0.0299 0.0526 1.0000
13.500 1.5008 0.02857 0.02227 -0.0289 0.0521 1.0000
13.750 1.5122 0.02969 0.02344 -0.0279 0.0514 1.0000
14.000 1.5226 0.03092 0.02472 -0.0269 0.0505 1.0000
14.250 1.5326 0.03220 0.02603 -0.0259 0.0497 1.0000
14.500 1.5401 0.03370 0.02757 -0.0249 0.0485 1.0000
14.750 1.5469 0.03529 0.02919 -0.0238 0.0472 1.0000
15.000 1.5537 0.03692 0.03086 -0.0229 0.0463 1.0000
15.250 1.5627 0.03840 0.03239 -0.0222 0.0458 1.0000
15.500 1.5711 0.03994 0.03399 -0.0214 0.0450 1.0000
15.750 1.5777 0.04169 0.03579 -0.0207 0.0444 1.0000
16.000 1.5840 0.04348 0.03764 -0.0201 0.0436 1.0000
16.250 1.5886 0.04549 0.03970 -0.0194 0.0428 1.0000
16.500 1.5924 0.04764 0.04189 -0.0189 0.0421 1.0000
16.750 1.5960 0.04985 0.04417 -0.0185 0.0417 1.0000
17.000 1.5977 0.05230 0.04667 -0.0181 0.0410 1.0000
17.250 1.6002 0.05473 0.04917 -0.0179 0.0405 1.0000
17.500 1.6035 0.05713 0.05164 -0.0177 0.0400 1.0000
17.750 1.6059 0.05968 0.05427 -0.0177 0.0396 1.0000
18.000 1.6075 0.06236 0.05701 -0.0177 0.0391 1.0000
18.250 1.6084 0.06513 0.05985 -0.0178 0.0384 1.0000
18.500 1.6082 0.06806 0.06285 -0.0180 0.0379 1.0000
18.750 1.6065 0.07121 0.06606 -0.0183 0.0372 1.0000
19.000 1.6039 0.07450 0.06942 -0.0187 0.0368 1.0000
19.250 1.6003 0.07792 0.07290 -0.0191 0.0360 1.0000
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Polar data table (+)
Polar graphs
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