GOE 63 AIRFOIL (goe63-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 63 AIRFOIL (goe63-il) Reynolds number: 200,000 Max Cl/Cd: 80.71 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe63-il-200000-n5.txt Download as CSV file: xf-goe63-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 63 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.1665 0.09643 0.09272 -0.0407 0.8710 0.0287
-7.750 -0.1603 0.09456 0.09076 -0.0438 0.8488 0.0289
-7.500 -0.1503 0.09211 0.08825 -0.0471 0.8328 0.0289
-7.250 -0.1394 0.08860 0.08468 -0.0460 0.8213 0.0291
-7.000 -0.1276 0.08569 0.08172 -0.0467 0.8103 0.0293
-6.750 -0.1144 0.08297 0.07895 -0.0484 0.8004 0.0296
-6.500 -0.0999 0.08032 0.07624 -0.0506 0.7912 0.0300
-6.250 -0.0836 0.07762 0.07351 -0.0534 0.7821 0.0304
-6.000 -0.0658 0.07492 0.07074 -0.0564 0.7739 0.0310
-5.750 -0.0460 0.07214 0.06792 -0.0599 0.7659 0.0316
-5.500 -0.0231 0.06933 0.06504 -0.0643 0.7587 0.0326
-5.250 0.0194 0.06645 0.06198 -0.0761 0.7519 0.0335
-5.000 0.0462 0.06328 0.05875 -0.0805 0.7450 0.0336
-4.750 0.0606 0.06033 0.05577 -0.0800 0.7391 0.0338
-4.500 0.0807 0.05767 0.05309 -0.0813 0.7330 0.0342
-4.250 0.1051 0.05513 0.05050 -0.0838 0.7271 0.0347
-4.000 0.1325 0.05264 0.04792 -0.0869 0.7220 0.0355
-3.750 0.1626 0.05013 0.04533 -0.0905 0.7163 0.0364
-3.500 0.1978 0.04759 0.04267 -0.0950 0.7098 0.0380
-3.250 0.2456 0.04476 0.03953 -0.1020 0.7040 0.0391
-3.000 0.2663 0.04240 0.03719 -0.1025 0.6969 0.0396
-2.750 0.2936 0.04034 0.03504 -0.1042 0.6898 0.0403
-2.500 0.3242 0.03835 0.03293 -0.1063 0.6835 0.0413
-2.250 0.3575 0.03637 0.03083 -0.1088 0.6766 0.0428
-2.000 0.4067 0.03473 0.02870 -0.1129 0.6701 0.0450
-1.750 0.4339 0.03229 0.02623 -0.1143 0.6630 0.0455
-1.500 0.4606 0.03055 0.02445 -0.1153 0.6555 0.0463
-1.250 0.4905 0.02911 0.02288 -0.1165 0.6496 0.0476
-1.000 0.5310 0.02800 0.02138 -0.1182 0.6437 0.0524
-0.750 0.5576 0.02624 0.01965 -0.1192 0.6379 0.0536
-0.500 0.5875 0.02504 0.01833 -0.1201 0.6324 0.0550
-0.250 0.6193 0.02392 0.01707 -0.1209 0.6258 0.0571
0.000 0.6603 0.02114 0.01366 -0.1218 0.6204 0.0391
0.250 0.6902 0.02020 0.01259 -0.1223 0.6147 0.0381
0.500 0.7209 0.01921 0.01146 -0.1228 0.6074 0.0376
0.750 0.7516 0.01831 0.01030 -0.1230 0.6007 0.0379
1.000 0.7824 0.01753 0.00924 -0.1231 0.5935 0.0389
1.250 0.8117 0.01686 0.00842 -0.1232 0.5858 0.0388
1.500 0.8407 0.01629 0.00772 -0.1232 0.5778 0.0388
1.750 0.8694 0.01579 0.00712 -0.1231 0.5685 0.0390
2.000 0.8977 0.01538 0.00668 -0.1231 0.5588 0.0395
2.250 0.9256 0.01510 0.00634 -0.1230 0.5483 0.0403
2.500 0.9534 0.01491 0.00617 -0.1229 0.5351 0.0424
2.750 0.9809 0.01475 0.00595 -0.1226 0.5200 0.0445
3.000 1.0082 0.01459 0.00575 -0.1224 0.5017 0.0456
3.250 1.0350 0.01454 0.00565 -0.1222 0.4803 0.0473
3.500 1.0613 0.01461 0.00562 -0.1219 0.4562 0.0496
3.750 1.0868 0.01478 0.00565 -0.1215 0.4320 0.0538
4.000 1.1121 0.01502 0.00577 -0.1210 0.4091 0.0604
4.250 1.1373 0.01529 0.00595 -0.1206 0.3888 0.0730
4.500 1.1550 0.01431 0.00627 -0.1187 0.3737 0.8740
4.750 1.1794 0.01462 0.00644 -0.1180 0.3589 1.0000
5.000 1.2041 0.01504 0.00672 -0.1175 0.3464 1.0000
5.250 1.2285 0.01547 0.00704 -0.1170 0.3351 1.0000
5.500 1.2533 0.01584 0.00735 -0.1166 0.3250 1.0000
5.750 1.2772 0.01629 0.00772 -0.1160 0.3159 1.0000
6.000 1.3019 0.01666 0.00806 -0.1155 0.3070 1.0000
6.250 1.3254 0.01711 0.00845 -0.1149 0.2990 1.0000
6.500 1.3497 0.01748 0.00884 -0.1144 0.2905 1.0000
6.750 1.3726 0.01795 0.00926 -0.1137 0.2824 1.0000
7.000 1.3964 0.01832 0.00966 -0.1131 0.2739 1.0000
7.250 1.4185 0.01882 0.01011 -0.1124 0.2663 1.0000
7.500 1.4418 0.01921 0.01056 -0.1117 0.2581 1.0000
7.750 1.4629 0.01973 0.01105 -0.1108 0.2499 1.0000
8.000 1.4850 0.02017 0.01152 -0.1100 0.2408 1.0000
8.250 1.5052 0.02071 0.01207 -0.1090 0.2324 1.0000
8.500 1.5256 0.02123 0.01262 -0.1080 0.2238 1.0000
8.750 1.5445 0.02182 0.01321 -0.1068 0.2162 1.0000
9.000 1.5629 0.02242 0.01385 -0.1055 0.2082 1.0000
9.250 1.5798 0.02308 0.01453 -0.1040 0.2010 1.0000
9.500 1.5956 0.02376 0.01524 -0.1024 0.1935 1.0000
9.750 1.6090 0.02453 0.01603 -0.1005 0.1868 1.0000
10.000 1.6205 0.02531 0.01684 -0.0982 0.1798 1.0000
10.250 1.6297 0.02629 0.01783 -0.0958 0.1736 1.0000
10.500 1.6414 0.02719 0.01880 -0.0939 0.1673 1.0000
10.750 1.6496 0.02836 0.01998 -0.0918 0.1614 1.0000
11.000 1.6603 0.02945 0.02114 -0.0901 0.1559 1.0000
11.250 1.6695 0.03069 0.02245 -0.0885 0.1505 1.0000
11.500 1.6755 0.03224 0.02400 -0.0867 0.1460 1.0000
11.750 1.6866 0.03346 0.02535 -0.0855 0.1416 1.0000
12.000 1.6949 0.03496 0.02692 -0.0842 0.1371 1.0000
12.250 1.7002 0.03676 0.02876 -0.0829 0.1331 1.0000
12.500 1.7084 0.03836 0.03048 -0.0818 0.1292 1.0000
12.750 1.7157 0.04008 0.03229 -0.0808 0.1249 1.0000
13.000 1.7201 0.04211 0.03438 -0.0798 0.1211 1.0000
13.250 1.7239 0.04425 0.03659 -0.0789 0.1178 1.0000
13.500 1.7307 0.04612 0.03860 -0.0781 0.1143 1.0000
13.750 1.7346 0.04830 0.04090 -0.0773 0.1108 1.0000
14.000 1.7354 0.05086 0.04353 -0.0766 0.1074 1.0000
14.250 1.7378 0.05330 0.04608 -0.0760 0.1038 1.0000
14.500 1.7401 0.05578 0.04868 -0.0755 0.0996 1.0000
14.750 1.7383 0.05878 0.05176 -0.0751 0.0957 1.0000
15.000 1.7375 0.06174 0.05484 -0.0748 0.0919 1.0000
15.250 1.7362 0.06485 0.05806 -0.0746 0.0866 1.0000
15.500 1.7309 0.06858 0.06186 -0.0747 0.0814 1.0000
15.750 1.7267 0.07223 0.06562 -0.0749 0.0753 1.0000
16.000 1.7186 0.07654 0.07001 -0.0753 0.0680 1.0000
16.250 1.7062 0.08159 0.07511 -0.0761 0.0589 1.0000
16.500 1.6894 0.08742 0.08097 -0.0772 0.0491 1.0000
16.750 1.6680 0.09418 0.08775 -0.0789 0.0403 1.0000
17.000 1.6455 0.10135 0.09497 -0.0810 0.0338 1.0000
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Polar data table (+)
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