GOE 301 (FRIEDRICHSHAFEN G 13) AIRFOIL (goe301-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 301 (FRIEDRICHSHAFEN G 13) AIRFOIL (goe301-il) Reynolds number: 500,000 Max Cl/Cd: 108.5 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe301-il-500000-n5.txt Download as CSV file: xf-goe301-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 301 (FRIEDRICHSHAFEN G 13) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.2706 0.13207 0.12968 -0.0326 1.0000 0.0106
-11.500 -0.2671 0.12947 0.12710 -0.0327 1.0000 0.0108
-11.250 -0.2648 0.12667 0.12432 -0.0328 1.0000 0.0109
-11.000 -0.2550 0.12297 0.12062 -0.0352 0.9990 0.0109
-10.750 -0.2426 0.11903 0.11669 -0.0383 0.9974 0.0111
-10.500 -0.2301 0.11511 0.11277 -0.0415 0.9957 0.0113
-10.250 -0.2181 0.11116 0.10881 -0.0447 0.9939 0.0115
-10.000 -0.2077 0.10713 0.10477 -0.0477 0.9909 0.0119
-9.750 -0.1977 0.10267 0.10032 -0.0512 0.9878 0.0126
-9.250 -0.1694 0.09700 0.09466 -0.0564 0.9789 0.0132
-9.000 -0.1567 0.09356 0.09123 -0.0594 0.9722 0.0135
-8.500 -0.1284 0.08588 0.08353 -0.0669 0.9510 0.0143
-8.250 -0.1158 0.08015 0.07776 -0.0732 0.9343 0.0154
-8.000 -0.0934 0.07778 0.07532 -0.0767 0.9139 0.0157
-7.750 -0.0793 0.07530 0.07273 -0.0791 0.8898 0.0161
-7.500 -0.0676 0.07241 0.06976 -0.0819 0.8641 0.0165
-7.250 -0.0546 0.06912 0.06635 -0.0855 0.8353 0.0170
-7.000 -0.0404 0.06205 0.05912 -0.0952 0.8028 0.0184
-6.750 -0.0230 0.06065 0.05754 -0.0964 0.7694 0.0187
-6.250 0.0168 0.05620 0.05281 -0.1021 0.7280 0.0197
-6.000 0.0407 0.05253 0.04902 -0.1072 0.7148 0.0204
-5.750 0.0739 0.04490 0.04117 -0.1181 0.7049 0.0222
-5.500 0.0971 0.04363 0.03981 -0.1193 0.6944 0.0225
-5.250 0.1230 0.04148 0.03756 -0.1217 0.6849 0.0230
-5.000 0.1511 0.03854 0.03446 -0.1249 0.6771 0.0236
-4.750 0.1820 0.03473 0.03045 -0.1287 0.6698 0.0246
-4.500 0.2184 0.02643 0.02159 -0.1346 0.6639 0.0263
-4.250 0.2456 0.02475 0.01973 -0.1355 0.6568 0.0267
-4.000 0.2725 0.02372 0.01858 -0.1359 0.6492 0.0272
-3.750 0.3000 0.02230 0.01698 -0.1365 0.6427 0.0279
-3.500 0.3296 0.01884 0.01307 -0.1376 0.6367 0.0288
-3.250 0.3584 0.01431 0.00771 -0.1384 0.6311 0.0304
-3.000 0.3862 0.01342 0.00655 -0.1385 0.6248 0.0310
-2.750 0.4138 0.01278 0.00578 -0.1385 0.6177 0.0316
-2.500 0.4413 0.01244 0.00533 -0.1383 0.6108 0.0321
-2.250 0.4692 0.01213 0.00495 -0.1383 0.6041 0.0326
-2.000 0.4968 0.01186 0.00459 -0.1382 0.5973 0.0331
-1.750 0.5245 0.01159 0.00425 -0.1380 0.5905 0.0337
-1.500 0.5521 0.01134 0.00393 -0.1379 0.5824 0.0344
-1.250 0.5796 0.01113 0.00365 -0.1377 0.5748 0.0352
-1.000 0.6071 0.01098 0.00343 -0.1376 0.5665 0.0361
-0.750 0.6346 0.01083 0.00323 -0.1374 0.5583 0.0370
-0.500 0.6618 0.01069 0.00306 -0.1373 0.5486 0.0381
-0.250 0.6892 0.01063 0.00297 -0.1371 0.5384 0.0392
0.000 0.7162 0.01060 0.00289 -0.1369 0.5261 0.0405
0.250 0.7427 0.01060 0.00281 -0.1365 0.5102 0.0420
0.500 0.7692 0.01064 0.00275 -0.1362 0.4941 0.0435
0.750 0.7957 0.01067 0.00275 -0.1359 0.4811 0.0463
1.000 0.8225 0.01073 0.00278 -0.1357 0.4702 0.0497
1.250 0.8491 0.01080 0.00279 -0.1354 0.4588 0.0531
1.500 0.8754 0.01090 0.00286 -0.1351 0.4467 0.0573
2.000 0.9282 0.01110 0.00299 -0.1345 0.4257 0.0667
2.250 0.9544 0.01124 0.00308 -0.1342 0.4177 0.0720
2.500 0.9812 0.01130 0.00315 -0.1340 0.4103 0.0795
2.750 1.0075 0.01142 0.00325 -0.1337 0.4036 0.0873
3.000 1.0342 0.01148 0.00336 -0.1335 0.3975 0.1059
3.500 1.0829 0.01029 0.00382 -0.1326 0.3845 1.0000
3.750 1.1094 0.01044 0.00394 -0.1324 0.3781 1.0000
4.000 1.1352 0.01064 0.00409 -0.1320 0.3715 1.0000
4.250 1.1612 0.01082 0.00423 -0.1317 0.3643 1.0000
4.500 1.1867 0.01103 0.00440 -0.1313 0.3564 1.0000
4.750 1.2124 0.01122 0.00456 -0.1310 0.3501 1.0000
5.000 1.2379 0.01142 0.00474 -0.1306 0.3428 1.0000
5.250 1.2629 0.01164 0.00494 -0.1301 0.3357 1.0000
5.500 1.2878 0.01187 0.00514 -0.1297 0.3269 1.0000
5.750 1.3123 0.01212 0.00535 -0.1291 0.3177 1.0000
6.000 1.3361 0.01241 0.00560 -0.1285 0.3073 1.0000
6.250 1.3601 0.01267 0.00584 -0.1279 0.2976 1.0000
6.500 1.3836 0.01297 0.00611 -0.1273 0.2885 1.0000
7.000 1.4293 0.01360 0.00670 -0.1257 0.2693 1.0000
7.250 1.4514 0.01396 0.00703 -0.1249 0.2609 1.0000
7.500 1.4736 0.01429 0.00735 -0.1240 0.2526 1.0000
7.750 1.4949 0.01466 0.00772 -0.1230 0.2451 1.0000
8.000 1.5163 0.01501 0.00808 -0.1221 0.2377 1.0000
8.250 1.5364 0.01542 0.00848 -0.1209 0.2308 1.0000
8.500 1.5569 0.01578 0.00887 -0.1197 0.2239 1.0000
8.750 1.5741 0.01627 0.00934 -0.1181 0.2145 1.0000
9.000 1.5888 0.01685 0.00986 -0.1160 0.2016 1.0000
9.250 1.6035 0.01744 0.01041 -0.1140 0.1876 1.0000
9.500 1.6174 0.01808 0.01102 -0.1119 0.1735 1.0000
9.750 1.6297 0.01883 0.01170 -0.1096 0.1580 1.0000
10.000 1.6403 0.01968 0.01248 -0.1071 0.1434 1.0000
10.250 1.6503 0.02058 0.01334 -0.1047 0.1329 1.0000
10.500 1.6620 0.02139 0.01416 -0.1026 0.1257 1.0000
10.750 1.6719 0.02233 0.01511 -0.1003 0.1195 1.0000
11.000 1.6848 0.02312 0.01596 -0.0985 0.1158 1.0000
11.250 1.6954 0.02407 0.01694 -0.0966 0.1111 1.0000
11.500 1.7033 0.02525 0.01814 -0.0944 0.1058 1.0000
11.750 1.7147 0.02622 0.01918 -0.0928 0.1011 1.0000
12.000 1.7216 0.02756 0.02054 -0.0908 0.0936 1.0000
12.250 1.7279 0.02901 0.02200 -0.0889 0.0821 1.0000
12.500 1.7146 0.03214 0.02493 -0.0857 0.0557 1.0000
12.750 1.7084 0.03491 0.02770 -0.0835 0.0447 1.0000
13.000 1.7033 0.03777 0.03058 -0.0818 0.0358 1.0000
13.250 1.6964 0.04099 0.03381 -0.0803 0.0261 1.0000
13.750 1.6856 0.04752 0.04044 -0.0784 0.0176 1.0000
14.000 1.6818 0.05076 0.04377 -0.0777 0.0160 1.0000
14.250 1.6795 0.05391 0.04703 -0.0773 0.0150 1.0000
14.500 1.6753 0.05733 0.05055 -0.0769 0.0141 1.0000
14.750 1.6695 0.06105 0.05437 -0.0766 0.0134 1.0000
15.000 1.6629 0.06494 0.05836 -0.0765 0.0128 1.0000
15.250 1.6585 0.06863 0.06217 -0.0765 0.0124 1.0000
15.500 1.6525 0.07258 0.06624 -0.0767 0.0119 1.0000
15.750 1.6453 0.07679 0.07056 -0.0770 0.0115 1.0000
16.000 1.6370 0.08126 0.07515 -0.0775 0.0111 1.0000
16.250 1.6278 0.08593 0.07992 -0.0782 0.0108 1.0000
16.500 1.6177 0.09080 0.08491 -0.0789 0.0105 1.0000
16.750 1.6064 0.09593 0.09015 -0.0799 0.0102 1.0000
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