GOE 366 AIRFOIL (goe366-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 366 AIRFOIL (goe366-il) Reynolds number: 1,000,000 Max Cl/Cd: 121.12 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe366-il-1000000-n5.txt Download as CSV file: xf-goe366-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 366 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 -0.0356 0.11143 0.10880 -0.0828 0.7997 0.0156
-10.750 -0.0282 0.10858 0.10589 -0.0841 0.7868 0.0157
-10.500 -0.0207 0.10578 0.10302 -0.0854 0.7741 0.0157
-10.250 -0.0130 0.10298 0.10016 -0.0868 0.7632 0.0157
-10.000 -0.0053 0.10018 0.09733 -0.0883 0.7550 0.0157
-9.750 0.0024 0.09736 0.09448 -0.0898 0.7481 0.0157
-9.250 0.0197 0.09207 0.08914 -0.0923 0.7362 0.0158
-9.000 0.0297 0.08980 0.08685 -0.0932 0.7303 0.0159
-8.500 0.0499 0.08538 0.08239 -0.0955 0.7195 0.0161
-8.250 0.0602 0.08313 0.08013 -0.0968 0.7143 0.0164
-8.000 0.0702 0.08080 0.07778 -0.0983 0.7092 0.0166
-7.750 0.0799 0.07839 0.07535 -0.0998 0.7046 0.0169
-7.500 0.0899 0.07582 0.07280 -0.1016 0.7012 0.0175
-7.250 0.0990 0.07302 0.06999 -0.1038 0.6972 0.0177
-7.000 0.1079 0.07034 0.06730 -0.1064 0.6930 0.0178
-6.750 0.1223 0.06728 0.06423 -0.1105 0.6886 0.0178
-6.500 0.1390 0.06410 0.06102 -0.1151 0.6848 0.0179
-6.250 0.1580 0.06078 0.05769 -0.1200 0.6807 0.0179
-6.000 0.1803 0.05699 0.05385 -0.1261 0.6760 0.0179
-5.750 0.2029 0.05346 0.05025 -0.1310 0.6708 0.0180
-5.500 0.2255 0.05012 0.04686 -0.1349 0.6661 0.0180
-5.250 0.2445 0.04805 0.04476 -0.1362 0.6603 0.0181
-5.000 0.2658 0.04596 0.04262 -0.1381 0.6534 0.0182
-4.750 0.2888 0.04384 0.04044 -0.1402 0.6464 0.0183
-4.500 0.3130 0.04169 0.03822 -0.1424 0.6365 0.0185
-4.250 0.3381 0.03952 0.03595 -0.1444 0.6257 0.0188
-4.000 0.3635 0.03738 0.03369 -0.1463 0.6115 0.0192
-3.750 0.3918 0.03482 0.03092 -0.1483 0.5905 0.0201
-3.500 0.4190 0.03229 0.02813 -0.1496 0.5664 0.0203
-3.250 0.4455 0.02991 0.02551 -0.1504 0.5456 0.0203
-3.000 0.4710 0.02782 0.02320 -0.1509 0.5295 0.0203
-2.750 0.4969 0.02580 0.02098 -0.1512 0.5175 0.0203
-2.500 0.5233 0.02390 0.01889 -0.1515 0.5081 0.0204
-2.250 0.5491 0.02232 0.01712 -0.1516 0.4983 0.0203
-2.000 0.5741 0.02126 0.01595 -0.1518 0.4900 0.0202
-1.750 0.5994 0.02025 0.01482 -0.1519 0.4811 0.0201
-1.500 0.6263 0.01906 0.01347 -0.1519 0.4744 0.0199
-1.250 0.6537 0.01780 0.01202 -0.1518 0.4679 0.0200
-0.750 0.7083 0.01566 0.00951 -0.1515 0.4555 0.0199
-0.500 0.7357 0.01466 0.00831 -0.1513 0.4487 0.0199
-0.250 0.7629 0.01370 0.00709 -0.1509 0.4421 0.0202
0.000 0.7904 0.01307 0.00630 -0.1507 0.4369 0.0204
0.250 0.8172 0.01266 0.00580 -0.1506 0.4313 0.0206
0.500 0.8435 0.01243 0.00549 -0.1504 0.4255 0.0207
0.750 0.8704 0.01219 0.00521 -0.1502 0.4208 0.0209
1.000 0.8969 0.01204 0.00502 -0.1501 0.4150 0.0211
1.250 0.9228 0.01194 0.00485 -0.1497 0.4088 0.0214
1.500 0.9494 0.01176 0.00464 -0.1495 0.4042 0.0217
1.750 0.9760 0.01157 0.00441 -0.1493 0.3996 0.0218
2.000 1.0020 0.01145 0.00425 -0.1490 0.3947 0.0220
2.250 1.0277 0.01139 0.00414 -0.1487 0.3898 0.0223
2.500 1.0542 0.01132 0.00405 -0.1485 0.3858 0.0227
2.750 1.0801 0.01132 0.00403 -0.1482 0.3807 0.0230
3.000 1.1054 0.01132 0.00401 -0.1478 0.3754 0.0233
3.250 1.1309 0.01136 0.00405 -0.1475 0.3714 0.0237
3.500 1.1568 0.01139 0.00409 -0.1472 0.3677 0.0242
3.750 1.1819 0.01147 0.00417 -0.1469 0.3631 0.0251
4.000 1.2059 0.01160 0.00426 -0.1463 0.3574 0.0256
4.250 1.2308 0.01168 0.00435 -0.1458 0.3528 0.0260
4.500 1.2553 0.01177 0.00443 -0.1453 0.3476 0.0267
4.750 1.2788 0.01191 0.00456 -0.1447 0.3429 0.0274
5.000 1.3012 0.01206 0.00471 -0.1438 0.3390 0.0283
5.250 1.3236 0.01216 0.00483 -0.1429 0.3359 0.0297
5.500 1.3451 0.01231 0.00497 -0.1418 0.3318 0.0312
5.750 1.3662 0.01251 0.00516 -0.1407 0.3271 0.0326
6.000 1.3881 0.01273 0.00538 -0.1398 0.3229 0.0356
6.250 1.4135 0.01167 0.00594 -0.1400 0.3196 1.0000
6.500 1.4356 0.01191 0.00616 -0.1392 0.3151 1.0000
6.750 1.4566 0.01219 0.00642 -0.1382 0.3103 1.0000
7.000 1.4775 0.01248 0.00669 -0.1372 0.3067 1.0000
7.250 1.4998 0.01271 0.00693 -0.1364 0.3042 1.0000
7.500 1.5216 0.01297 0.00719 -0.1356 0.3012 1.0000
7.750 1.5425 0.01327 0.00749 -0.1347 0.2977 1.0000
8.000 1.5619 0.01364 0.00785 -0.1335 0.2930 1.0000
8.250 1.5820 0.01399 0.00819 -0.1325 0.2874 1.0000
8.500 1.6008 0.01440 0.00858 -0.1314 0.2804 1.0000
8.750 1.6187 0.01486 0.00902 -0.1301 0.2748 1.0000
9.000 1.6386 0.01523 0.00940 -0.1291 0.2703 1.0000
9.250 1.6566 0.01571 0.00987 -0.1280 0.2643 1.0000
9.500 1.6736 0.01625 0.01039 -0.1267 0.2586 1.0000
9.750 1.6908 0.01678 0.01092 -0.1254 0.2509 1.0000
10.000 1.7054 0.01746 0.01157 -0.1239 0.2425 1.0000
10.250 1.7198 0.01819 0.01226 -0.1223 0.2324 1.0000
10.500 1.7322 0.01903 0.01306 -0.1206 0.2207 1.0000
10.750 1.7396 0.02020 0.01413 -0.1183 0.2034 1.0000
11.000 1.7419 0.02174 0.01554 -0.1154 0.1810 1.0000
11.250 1.7378 0.02374 0.01738 -0.1120 0.1538 1.0000
11.500 1.7328 0.02592 0.01942 -0.1087 0.1308 1.0000
11.750 1.7362 0.02758 0.02104 -0.1065 0.1199 1.0000
12.000 1.7443 0.02893 0.02241 -0.1049 0.1141 1.0000
12.250 1.7499 0.03053 0.02400 -0.1031 0.1079 1.0000
12.500 1.7586 0.03193 0.02542 -0.1018 0.1034 1.0000
12.750 1.7636 0.03367 0.02716 -0.1002 0.0979 1.0000
13.000 1.7695 0.03538 0.02890 -0.0988 0.0933 1.0000
13.250 1.7755 0.03712 0.03066 -0.0976 0.0882 1.0000
13.500 1.7780 0.03923 0.03277 -0.0961 0.0825 1.0000
13.750 1.7787 0.04156 0.03511 -0.0947 0.0750 1.0000
14.000 1.7751 0.04436 0.03788 -0.0932 0.0664 1.0000
14.250 1.7686 0.04752 0.04104 -0.0916 0.0578 1.0000
14.500 1.7617 0.05085 0.04437 -0.0902 0.0504 1.0000
15.000 1.7298 0.05982 0.05335 -0.0875 0.0299 1.0000
15.250 1.7073 0.06542 0.05897 -0.0864 0.0194 1.0000
15.500 1.6984 0.06952 0.06314 -0.0859 0.0169 1.0000
15.750 1.6917 0.07340 0.06710 -0.0856 0.0157 1.0000
16.000 1.6860 0.07724 0.07103 -0.0855 0.0149 1.0000
16.250 1.6812 0.08101 0.07488 -0.0854 0.0144 1.0000
16.500 1.6754 0.08494 0.07890 -0.0855 0.0139 1.0000
16.750 1.6684 0.08903 0.08307 -0.0856 0.0135 1.0000
17.000 1.6609 0.09322 0.08735 -0.0858 0.0131 1.0000
17.250 1.6537 0.09742 0.09162 -0.0861 0.0127 1.0000
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