GOE 366 AIRFOIL (goe366-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 366 AIRFOIL (goe366-il) Reynolds number: 100,000 Max Cl/Cd: 55.01 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe366-il-100000-n5.txt Download as CSV file: xf-goe366-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 0.0156 0.10332 0.09807 -0.0932 0.9299 0.0451
-8.750 0.0235 0.10101 0.09576 -0.0960 0.9212 0.0456
-8.250 0.0499 0.09489 0.08963 -0.1000 0.9077 0.0464
-8.000 0.0651 0.09184 0.08657 -0.1017 0.9010 0.0473
-7.750 0.0756 0.08930 0.08402 -0.1029 0.8921 0.0482
-7.500 0.0854 0.08680 0.08150 -0.1045 0.8832 0.0492
-7.250 0.0902 0.08473 0.07943 -0.1056 0.8731 0.0502
-7.000 0.0953 0.08273 0.07741 -0.1092 0.8641 0.0510
-6.750 0.1023 0.08038 0.07507 -0.1111 0.8552 0.0515
-6.500 0.1154 0.07762 0.07232 -0.1102 0.8491 0.0525
-6.250 0.1309 0.07497 0.06963 -0.1123 0.8437 0.0542
-6.000 0.1386 0.07298 0.06765 -0.1141 0.8340 0.0559
-5.750 0.1635 0.07016 0.06465 -0.1246 0.8275 0.0574
-5.500 0.1690 0.06774 0.06230 -0.1214 0.8192 0.0579
-5.250 0.1846 0.06514 0.05969 -0.1215 0.8134 0.0591
-5.000 0.2020 0.06274 0.05724 -0.1231 0.8068 0.0609
-4.750 0.2294 0.06049 0.05476 -0.1300 0.7985 0.0642
-4.500 0.2503 0.05729 0.05152 -0.1312 0.7939 0.0652
-4.250 0.2616 0.05531 0.04957 -0.1300 0.7853 0.0665
-4.000 0.2861 0.05293 0.04708 -0.1320 0.7792 0.0695
-3.750 0.3173 0.05052 0.04441 -0.1364 0.7723 0.0735
-3.500 0.3333 0.04832 0.04224 -0.1356 0.7647 0.0757
-3.250 0.3724 0.04624 0.03978 -0.1402 0.7593 0.0834
-3.000 0.3849 0.04415 0.03778 -0.1388 0.7502 0.0854
-2.500 0.4396 0.04031 0.03360 -0.1414 0.7353 0.0969
-2.250 0.4652 0.03864 0.03182 -0.1420 0.7273 0.1029
-2.000 0.4936 0.03682 0.02981 -0.1432 0.7198 0.1114
-1.750 0.5201 0.03561 0.02838 -0.1437 0.7103 0.1243
-1.500 0.5465 0.03387 0.02658 -0.1442 0.7024 0.1312
-1.250 0.5692 0.03261 0.02523 -0.1440 0.6920 0.1459
-0.750 0.6421 0.02942 0.02084 -0.1440 0.6733 0.0724
-0.500 0.6695 0.02779 0.01902 -0.1438 0.6634 0.0633
-0.250 0.6979 0.02665 0.01751 -0.1433 0.6529 0.0569
0.000 0.7219 0.02575 0.01652 -0.1426 0.6410 0.0551
0.250 0.7499 0.02487 0.01536 -0.1422 0.6304 0.0527
0.500 0.7762 0.02426 0.01444 -0.1414 0.6186 0.0508
0.750 0.8008 0.02368 0.01373 -0.1407 0.6066 0.0502
1.000 0.8272 0.02315 0.01302 -0.1401 0.5955 0.0501
1.250 0.8536 0.02275 0.01239 -0.1396 0.5845 0.0509
1.500 0.8785 0.02241 0.01193 -0.1389 0.5735 0.0515
1.750 0.9048 0.02208 0.01145 -0.1384 0.5639 0.0515
2.000 0.9296 0.02184 0.01113 -0.1377 0.5539 0.0515
2.250 0.9544 0.02164 0.01088 -0.1371 0.5448 0.0518
2.500 0.9788 0.02153 0.01069 -0.1364 0.5359 0.0523
2.750 1.0034 0.02152 0.01059 -0.1358 0.5277 0.0533
3.000 1.0283 0.02160 0.01057 -0.1353 0.5197 0.0557
3.250 1.0547 0.02172 0.01053 -0.1350 0.5126 0.0582
3.500 1.0784 0.02191 0.01067 -0.1344 0.5047 0.0602
3.750 1.1049 0.02210 0.01070 -0.1342 0.4980 0.0629
4.000 1.1286 0.02236 0.01093 -0.1336 0.4910 0.0672
4.250 1.1529 0.02262 0.01116 -0.1331 0.4844 0.0797
4.750 1.1970 0.02183 0.01179 -0.1312 0.4729 1.0000
5.000 1.2197 0.02225 0.01210 -0.1305 0.4666 1.0000
5.250 1.2455 0.02264 0.01232 -0.1302 0.4614 1.0000
5.500 1.2667 0.02311 0.01278 -0.1293 0.4556 1.0000
5.750 1.2885 0.02357 0.01321 -0.1285 0.4501 1.0000
6.000 1.3124 0.02400 0.01356 -0.1281 0.4454 1.0000
6.250 1.3366 0.02446 0.01395 -0.1277 0.4408 1.0000
6.500 1.3550 0.02500 0.01454 -0.1264 0.4353 1.0000
6.750 1.3762 0.02548 0.01501 -0.1256 0.4303 1.0000
7.000 1.4005 0.02593 0.01540 -0.1253 0.4261 1.0000
7.250 1.4206 0.02649 0.01599 -0.1243 0.4218 1.0000
7.500 1.4382 0.02710 0.01667 -0.1230 0.4172 1.0000
7.750 1.4576 0.02764 0.01724 -0.1219 0.4128 1.0000
8.000 1.4805 0.02812 0.01769 -0.1214 0.4090 1.0000
8.250 1.4988 0.02872 0.01834 -0.1202 0.4050 1.0000
8.500 1.5113 0.02946 0.01919 -0.1182 0.4005 1.0000
8.750 1.5284 0.03011 0.01991 -0.1169 0.3965 1.0000
9.000 1.5492 0.03066 0.02048 -0.1161 0.3929 1.0000
9.250 1.5689 0.03123 0.02105 -0.1152 0.3889 1.0000
9.500 1.5735 0.03220 0.02220 -0.1122 0.3837 1.0000
9.750 1.5855 0.03294 0.02300 -0.1103 0.3786 1.0000
10.000 1.6054 0.03342 0.02347 -0.1094 0.3744 1.0000
10.250 1.6132 0.03441 0.02461 -0.1071 0.3699 1.0000
10.500 1.6179 0.03555 0.02589 -0.1045 0.3650 1.0000
10.750 1.6304 0.03636 0.02676 -0.1029 0.3605 1.0000
11.000 1.6515 0.03680 0.02718 -0.1023 0.3566 1.0000
11.250 1.6475 0.03847 0.02909 -0.0990 0.3517 1.0000
11.500 1.6503 0.03984 0.03060 -0.0966 0.3466 1.0000
11.750 1.6635 0.04058 0.03136 -0.0953 0.3417 1.0000
12.000 1.6666 0.04203 0.03293 -0.0931 0.3369 1.0000
12.250 1.6621 0.04408 0.03517 -0.0905 0.3317 1.0000
12.500 1.6688 0.04541 0.03661 -0.0889 0.3273 1.0000
12.750 1.6868 0.04596 0.03718 -0.0882 0.3236 1.0000
13.000 1.6722 0.04906 0.04053 -0.0854 0.3187 1.0000
13.250 1.6663 0.05160 0.04324 -0.0834 0.3138 1.0000
13.500 1.6750 0.05288 0.04460 -0.0823 0.3094 1.0000
13.750 1.6720 0.05526 0.04711 -0.0807 0.3046 1.0000
14.000 1.6496 0.05972 0.05181 -0.0788 0.2987 1.0000
14.250 1.6551 0.06136 0.05351 -0.0778 0.2932 1.0000
14.500 1.6387 0.06557 0.05789 -0.0766 0.2874 1.0000
14.750 1.6118 0.07134 0.06386 -0.0757 0.2807 1.0000
15.000 1.6288 0.07166 0.06417 -0.0751 0.2747 1.0000
15.250 1.5597 0.08378 0.07660 -0.0755 0.2666 1.0000
15.500 1.5837 0.08305 0.07587 -0.0748 0.2603 1.0000
15.750 1.4994 0.09876 0.09185 -0.0775 0.2496 1.0000
16.000 1.5413 0.09513 0.08818 -0.0761 0.2442 1.0000
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Polar data table (+)
Polar graphs
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