GOE 508 AIRFOIL (goe508-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 508 AIRFOIL (goe508-il) Reynolds number: 500,000 Max Cl/Cd: 97.84 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe508-il-500000-n5.txt Download as CSV file: xf-goe508-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 508 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
------ -------- --------- --------- -------- -------- --------
-14.000 -0.5214 0.04172 0.03769 -0.1458 0.8954 0.0286
-13.750 -0.5418 0.03534 0.03089 -0.1526 0.8637 0.0287
-13.500 -0.5567 0.03236 0.02764 -0.1530 0.8426 0.0287
-13.250 -0.5685 0.03028 0.02533 -0.1514 0.8280 0.0287
-13.000 -0.5763 0.02871 0.02360 -0.1488 0.8160 0.0289
-12.750 -0.5799 0.02747 0.02222 -0.1459 0.8070 0.0290
-12.500 -0.5807 0.02643 0.02107 -0.1426 0.7988 0.0291
-12.250 -0.5790 0.02564 0.02016 -0.1393 0.7917 0.0292
-12.000 -0.5709 0.02484 0.01928 -0.1370 0.7858 0.0294
-11.750 -0.5595 0.02410 0.01846 -0.1350 0.7797 0.0295
-11.500 -0.5465 0.02341 0.01765 -0.1331 0.7742 0.0297
-11.250 -0.5320 0.02268 0.01683 -0.1315 0.7689 0.0299
-11.000 -0.5160 0.02202 0.01609 -0.1299 0.7634 0.0301
-10.750 -0.4992 0.02138 0.01534 -0.1285 0.7582 0.0303
-10.500 -0.4810 0.02079 0.01465 -0.1271 0.7538 0.0305
-10.250 -0.4621 0.02018 0.01395 -0.1259 0.7490 0.0308
-10.000 -0.4427 0.01958 0.01325 -0.1247 0.7438 0.0310
-9.750 -0.4227 0.01903 0.01259 -0.1235 0.7387 0.0313
-9.500 -0.4019 0.01852 0.01197 -0.1225 0.7341 0.0316
-9.250 -0.3804 0.01799 0.01136 -0.1215 0.7293 0.0319
-9.000 -0.3585 0.01751 0.01077 -0.1205 0.7245 0.0322
-8.750 -0.3361 0.01707 0.01023 -0.1196 0.7199 0.0325
-8.500 -0.3136 0.01662 0.00970 -0.1187 0.7155 0.0328
-8.250 -0.2911 0.01615 0.00920 -0.1178 0.7106 0.0331
-8.000 -0.2677 0.01579 0.00880 -0.1170 0.7052 0.0336
-7.750 -0.2440 0.01549 0.00843 -0.1163 0.7002 0.0340
-7.500 -0.2196 0.01518 0.00809 -0.1156 0.6954 0.0345
-7.250 -0.1953 0.01486 0.00773 -0.1149 0.6904 0.0350
-7.000 -0.1710 0.01456 0.00736 -0.1142 0.6853 0.0355
-6.750 -0.1466 0.01428 0.00700 -0.1135 0.6807 0.0360
-6.500 -0.1216 0.01399 0.00667 -0.1129 0.6757 0.0365
-6.250 -0.0966 0.01373 0.00635 -0.1122 0.6702 0.0370
-6.000 -0.0727 0.01343 0.00601 -0.1115 0.6647 0.0376
-5.750 -0.0476 0.01318 0.00575 -0.1109 0.6594 0.0383
-5.500 -0.0223 0.01297 0.00551 -0.1103 0.6536 0.0390
-5.250 0.0028 0.01278 0.00527 -0.1097 0.6482 0.0398
-5.000 0.0283 0.01259 0.00504 -0.1091 0.6432 0.0408
-4.750 0.0542 0.01243 0.00484 -0.1086 0.6377 0.0417
-4.500 0.0791 0.01222 0.00462 -0.1079 0.6322 0.0430
-4.250 0.1045 0.01207 0.00444 -0.1074 0.6271 0.0442
-4.000 0.1303 0.01192 0.00427 -0.1069 0.6215 0.0455
-3.750 0.1559 0.01180 0.00410 -0.1063 0.6155 0.0469
-3.500 0.1808 0.01165 0.00392 -0.1056 0.6102 0.0485
-3.250 0.2067 0.01151 0.00378 -0.1051 0.6050 0.0504
-3.000 0.2325 0.01142 0.00366 -0.1046 0.5998 0.0524
-2.750 0.2576 0.01130 0.00352 -0.1040 0.5949 0.0551
-2.500 0.2834 0.01120 0.00342 -0.1035 0.5903 0.0584
-2.250 0.3088 0.01109 0.00332 -0.1029 0.5845 0.0628
-2.000 0.3334 0.01102 0.00324 -0.1021 0.5777 0.0686
-1.750 0.3585 0.01094 0.00319 -0.1015 0.5716 0.0797
-1.500 0.3839 0.01089 0.00316 -0.1010 0.5657 0.0918
-1.250 0.4092 0.01087 0.00314 -0.1004 0.5612 0.1017
-1.000 0.4345 0.01084 0.00311 -0.0998 0.5572 0.1096
-0.750 0.4604 0.01081 0.00309 -0.0993 0.5525 0.1168
-0.500 0.4854 0.01077 0.00308 -0.0987 0.5472 0.1252
-0.250 0.5101 0.01078 0.00307 -0.0980 0.5424 0.1329
0.000 0.5352 0.01076 0.00307 -0.0974 0.5385 0.1438
0.250 0.5603 0.01071 0.00308 -0.0968 0.5340 0.1606
0.500 0.5845 0.01067 0.00310 -0.0961 0.5290 0.1832
0.750 0.6079 0.01063 0.00313 -0.0952 0.5243 0.2162
1.000 0.6317 0.01054 0.00317 -0.0944 0.5203 0.2586
1.250 0.6550 0.01041 0.00322 -0.0936 0.5163 0.3201
1.500 0.6755 0.01015 0.00328 -0.0922 0.5120 0.4315
1.750 0.6924 0.00985 0.00336 -0.0901 0.5074 0.5736
2.000 0.7083 0.00956 0.00346 -0.0876 0.5034 0.7005
2.250 0.7255 0.00931 0.00359 -0.0852 0.4986 0.8219
2.500 0.7903 0.00942 0.00387 -0.0929 0.4911 0.9325
2.750 0.8500 0.00963 0.00403 -0.0998 0.4855 0.9602
3.000 0.8979 0.00981 0.00420 -0.1040 0.4799 0.9829
3.250 0.9529 0.01006 0.00438 -0.1099 0.4730 0.9983
3.500 0.9816 0.01020 0.00448 -0.1103 0.4674 1.0000
3.750 0.9996 0.01031 0.00458 -0.1083 0.4616 1.0000
4.000 1.0159 0.01045 0.00468 -0.1061 0.4557 1.0000
4.250 1.0330 0.01059 0.00479 -0.1040 0.4501 1.0000
4.500 1.0498 0.01073 0.00492 -0.1019 0.4432 1.0000
4.750 1.0631 0.01092 0.00506 -0.0990 0.4361 1.0000
5.000 1.0767 0.01106 0.00518 -0.0962 0.4281 1.0000
5.250 1.0858 0.01127 0.00535 -0.0926 0.4193 1.0000
5.500 1.0980 0.01148 0.00553 -0.0897 0.4082 1.0000
5.750 1.1085 0.01177 0.00576 -0.0865 0.3958 1.0000
6.000 1.1169 0.01217 0.00608 -0.0830 0.3796 1.0000
6.250 1.1233 0.01269 0.00650 -0.0794 0.3601 1.0000
6.500 1.1262 0.01340 0.00707 -0.0754 0.3365 1.0000
6.750 1.1312 0.01415 0.00770 -0.0720 0.3150 1.0000
7.000 1.1382 0.01491 0.00837 -0.0690 0.2979 1.0000
7.250 1.1430 0.01584 0.00919 -0.0660 0.2790 1.0000
7.500 1.1526 0.01663 0.00993 -0.0637 0.2676 1.0000
7.750 1.1626 0.01746 0.01070 -0.0616 0.2582 1.0000
8.000 1.1761 0.01815 0.01138 -0.0600 0.2521 1.0000
8.250 1.1884 0.01894 0.01215 -0.0584 0.2455 1.0000
8.750 1.2144 0.02054 0.01374 -0.0555 0.2359 1.0000
9.000 1.2264 0.02145 0.01463 -0.0541 0.2298 1.0000
9.250 1.2375 0.02244 0.01560 -0.0527 0.2251 1.0000
9.500 1.2506 0.02332 0.01650 -0.0515 0.2221 1.0000
9.750 1.2657 0.02410 0.01731 -0.0505 0.2199 1.0000
10.000 1.2800 0.02494 0.01818 -0.0495 0.2173 1.0000
10.250 1.2933 0.02587 0.01913 -0.0485 0.2149 1.0000
10.500 1.3057 0.02687 0.02015 -0.0474 0.2124 1.0000
10.750 1.3170 0.02797 0.02126 -0.0463 0.2099 1.0000
11.000 1.3275 0.02915 0.02245 -0.0452 0.2071 1.0000
11.250 1.3409 0.03014 0.02349 -0.0443 0.2051 1.0000
11.500 1.3548 0.03111 0.02451 -0.0436 0.2030 1.0000
11.750 1.3678 0.03216 0.02559 -0.0428 0.2004 1.0000
12.000 1.3793 0.03334 0.02681 -0.0419 0.1980 1.0000
12.250 1.3902 0.03458 0.02808 -0.0411 0.1955 1.0000
12.500 1.3988 0.03605 0.02956 -0.0402 0.1926 1.0000
12.750 1.4097 0.03734 0.03088 -0.0394 0.1895 1.0000
13.000 1.4218 0.03855 0.03214 -0.0388 0.1863 1.0000
13.250 1.4315 0.03998 0.03360 -0.0381 0.1813 1.0000
13.500 1.4382 0.04171 0.03533 -0.0373 0.1774 1.0000
13.750 1.4488 0.04310 0.03677 -0.0367 0.1735 1.0000
14.000 1.4587 0.04457 0.03828 -0.0362 0.1699 1.0000
14.250 1.4646 0.04644 0.04015 -0.0355 0.1639 1.0000
14.500 1.4720 0.04817 0.04192 -0.0349 0.1589 1.0000
14.750 1.4766 0.05020 0.04394 -0.0343 0.1515 1.0000
15.000 1.4807 0.05232 0.04607 -0.0338 0.1449 1.0000
15.250 1.4812 0.05481 0.04853 -0.0332 0.1369 1.0000
15.500 1.4837 0.05711 0.05085 -0.0327 0.1308 1.0000
15.750 1.4837 0.05970 0.05343 -0.0322 0.1245 1.0000
16.000 1.4837 0.06232 0.05606 -0.0318 0.1176 1.0000
16.250 1.4835 0.06501 0.05876 -0.0314 0.1124 1.0000
16.500 1.4844 0.06759 0.06135 -0.0311 0.1067 1.0000
16.750 1.4835 0.07040 0.06419 -0.0308 0.1024 1.0000
17.000 1.4866 0.07279 0.06662 -0.0307 0.0978 1.0000
17.250 1.4824 0.07605 0.06989 -0.0306 0.0899 1.0000
17.500 1.4805 0.07906 0.07291 -0.0305 0.0825 1.0000
17.750 1.4674 0.08343 0.07723 -0.0305 0.0705 1.0000
18.000 1.4611 0.08709 0.08090 -0.0307 0.0658 1.0000
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Polar data table (+)
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