GOE 508 AIRFOIL (goe508-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 508 AIRFOIL (goe508-il) Reynolds number: 1,000,000 Max Cl/Cd: 132.85 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe508-il-1000000.txt Download as CSV file: xf-goe508-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.5962 0.04211 0.03930 -0.1352 0.9480 0.0286
-14.000 -0.5780 0.03298 0.02969 -0.1552 0.9223 0.0288
-13.750 -0.5806 0.03009 0.02645 -0.1577 0.8810 0.0289
-13.500 -0.5911 0.02841 0.02454 -0.1553 0.8566 0.0289
-13.250 -0.5970 0.02727 0.02321 -0.1523 0.8407 0.0290
-12.750 -0.6047 0.02524 0.02088 -0.1449 0.8190 0.0291
-12.500 -0.6039 0.02457 0.02006 -0.1411 0.8105 0.0292
-12.250 -0.6062 0.02292 0.01823 -0.1377 0.8035 0.0294
-12.000 -0.6006 0.02160 0.01678 -0.1350 0.7968 0.0296
-11.750 -0.5879 0.02080 0.01588 -0.1330 0.7907 0.0298
-11.500 -0.5717 0.02014 0.01516 -0.1315 0.7859 0.0300
-11.250 -0.5540 0.01957 0.01454 -0.1301 0.7806 0.0303
-11.000 -0.5356 0.01904 0.01393 -0.1287 0.7753 0.0305
-10.750 -0.5164 0.01856 0.01336 -0.1274 0.7699 0.0307
-10.500 -0.4962 0.01802 0.01277 -0.1263 0.7655 0.0310
-10.250 -0.4756 0.01751 0.01220 -0.1252 0.7607 0.0312
-10.000 -0.4547 0.01703 0.01163 -0.1240 0.7559 0.0315
-9.750 -0.4329 0.01663 0.01113 -0.1230 0.7511 0.0318
-9.500 -0.4109 0.01611 0.01057 -0.1221 0.7471 0.0321
-9.250 -0.3877 0.01575 0.01014 -0.1213 0.7423 0.0325
-9.000 -0.3648 0.01536 0.00965 -0.1204 0.7373 0.0328
-8.750 -0.3410 0.01507 0.00928 -0.1196 0.7324 0.0330
-8.500 -0.3166 0.01474 0.00890 -0.1189 0.7283 0.0332
-8.250 -0.2965 0.01387 0.00797 -0.1177 0.7236 0.0337
-8.000 -0.2734 0.01345 0.00751 -0.1168 0.7188 0.0342
-7.750 -0.2493 0.01315 0.00715 -0.1161 0.7140 0.0346
-7.500 -0.2240 0.01286 0.00686 -0.1155 0.7099 0.0350
-7.250 -0.1989 0.01258 0.00655 -0.1149 0.7048 0.0355
-7.000 -0.1741 0.01233 0.00624 -0.1142 0.6997 0.0360
-6.750 -0.1488 0.01209 0.00596 -0.1136 0.6946 0.0365
-6.500 -0.1230 0.01185 0.00568 -0.1131 0.6897 0.0370
-6.250 -0.0972 0.01166 0.00544 -0.1126 0.6844 0.0374
-6.000 -0.0735 0.01131 0.00502 -0.1117 0.6789 0.0381
-5.750 -0.0482 0.01100 0.00472 -0.1112 0.6743 0.0388
-5.500 -0.0221 0.01082 0.00453 -0.1107 0.6689 0.0397
-5.250 0.0037 0.01069 0.00435 -0.1102 0.6632 0.0406
-5.000 0.0299 0.01053 0.00417 -0.1097 0.6579 0.0415
-4.750 0.0565 0.01040 0.00400 -0.1093 0.6520 0.0422
-4.500 0.0809 0.01013 0.00369 -0.1085 0.6459 0.0434
-4.250 0.1068 0.00997 0.00353 -0.1080 0.6403 0.0447
-4.000 0.1333 0.00984 0.00339 -0.1076 0.6346 0.0460
-3.750 0.1594 0.00976 0.00326 -0.1071 0.6286 0.0473
-3.500 0.1848 0.00958 0.00306 -0.1065 0.6229 0.0492
-3.250 0.2111 0.00945 0.00293 -0.1060 0.6167 0.0513
-3.000 0.2368 0.00941 0.00283 -0.1055 0.6096 0.0532
-2.750 0.2624 0.00924 0.00268 -0.1049 0.6030 0.0566
-2.500 0.2885 0.00917 0.00258 -0.1044 0.5965 0.0596
-2.250 0.3134 0.00908 0.00248 -0.1037 0.5905 0.0649
-2.000 0.3398 0.00896 0.00241 -0.1033 0.5859 0.0740
-1.750 0.3656 0.00887 0.00238 -0.1028 0.5804 0.0910
-1.500 0.3910 0.00886 0.00237 -0.1022 0.5743 0.1028
-1.250 0.4173 0.00880 0.00234 -0.1018 0.5689 0.1121
-1.000 0.4437 0.00878 0.00232 -0.1014 0.5638 0.1192
-0.750 0.4694 0.00876 0.00230 -0.1009 0.5592 0.1268
-0.500 0.4948 0.00876 0.00230 -0.1003 0.5546 0.1348
-0.250 0.5215 0.00871 0.00229 -0.1000 0.5506 0.1443
0.000 0.5472 0.00867 0.00228 -0.0995 0.5460 0.1603
0.250 0.5717 0.00861 0.00230 -0.0988 0.5415 0.1887
0.500 0.5957 0.00854 0.00233 -0.0980 0.5371 0.2330
0.750 0.6203 0.00836 0.00235 -0.0974 0.5337 0.2955
1.000 0.6428 0.00813 0.00238 -0.0964 0.5293 0.3928
1.250 0.6615 0.00779 0.00244 -0.0947 0.5251 0.5425
1.500 0.6763 0.00747 0.00253 -0.0920 0.5203 0.6987
1.750 0.6906 0.00706 0.00265 -0.0888 0.5169 0.8618
2.000 0.7622 0.00715 0.00288 -0.0981 0.5107 0.9540
2.250 0.8099 0.00733 0.00300 -0.1023 0.5056 0.9687
2.500 0.8447 0.00749 0.00312 -0.1038 0.5015 0.9789
2.750 0.8848 0.00758 0.00320 -0.1064 0.4976 0.9836
3.000 0.9230 0.00771 0.00329 -0.1086 0.4930 0.9882
3.250 0.9632 0.00789 0.00342 -0.1113 0.4880 0.9935
3.750 1.0560 0.00811 0.00358 -0.1194 0.4779 1.0000
4.000 1.0743 0.00820 0.00365 -0.1175 0.4729 1.0000
4.250 1.0914 0.00833 0.00375 -0.1155 0.4678 1.0000
4.500 1.1115 0.00839 0.00381 -0.1139 0.4629 1.0000
4.750 1.1292 0.00850 0.00390 -0.1119 0.4564 1.0000
5.000 1.1454 0.00865 0.00401 -0.1096 0.4493 1.0000
5.250 1.1623 0.00878 0.00412 -0.1075 0.4400 1.0000
5.500 1.1766 0.00896 0.00425 -0.1048 0.4294 1.0000
5.750 1.1856 0.00918 0.00441 -0.1011 0.4161 1.0000
6.000 1.1915 0.00942 0.00458 -0.0968 0.4010 1.0000
6.250 1.1978 0.00975 0.00482 -0.0927 0.3812 1.0000
6.500 1.2018 0.01024 0.00518 -0.0883 0.3560 1.0000
6.750 1.2037 0.01091 0.00568 -0.0838 0.3268 1.0000
7.000 1.2074 0.01162 0.00624 -0.0799 0.3020 1.0000
7.250 1.2158 0.01224 0.00678 -0.0768 0.2845 1.0000
7.500 1.2249 0.01290 0.00735 -0.0741 0.2697 1.0000
7.750 1.2377 0.01346 0.00787 -0.0720 0.2598 1.0000
8.000 1.2503 0.01407 0.00843 -0.0699 0.2509 1.0000
8.250 1.2647 0.01463 0.00898 -0.0683 0.2451 1.0000
8.500 1.2779 0.01529 0.00961 -0.0665 0.2394 1.0000
8.750 1.2947 0.01581 0.01014 -0.0653 0.2362 1.0000
9.000 1.3110 0.01636 0.01070 -0.0640 0.2330 1.0000
9.250 1.3260 0.01701 0.01135 -0.0627 0.2295 1.0000
9.500 1.3393 0.01778 0.01212 -0.0613 0.2257 1.0000
9.750 1.3525 0.01858 0.01291 -0.0599 0.2223 1.0000
10.000 1.3701 0.01915 0.01352 -0.0590 0.2207 1.0000
10.250 1.3867 0.01978 0.01418 -0.0581 0.2188 1.0000
10.500 1.4019 0.02052 0.01495 -0.0571 0.2166 1.0000
10.750 1.4160 0.02135 0.01578 -0.0560 0.2141 1.0000
11.000 1.4280 0.02231 0.01675 -0.0548 0.2110 1.0000
11.250 1.4367 0.02352 0.01796 -0.0533 0.2069 1.0000
11.500 1.4539 0.02419 0.01867 -0.0526 0.2057 1.0000
11.750 1.4703 0.02491 0.01943 -0.0520 0.2027 1.0000
12.000 1.4838 0.02585 0.02040 -0.0510 0.2004 1.0000
12.250 1.4958 0.02690 0.02146 -0.0500 0.1976 1.0000
12.500 1.5047 0.02820 0.02276 -0.0489 0.1940 1.0000
12.750 1.5159 0.02936 0.02396 -0.0479 0.1913 1.0000
13.000 1.5314 0.03022 0.02486 -0.0474 0.1887 1.0000
13.250 1.5442 0.03127 0.02593 -0.0466 0.1852 1.0000
13.500 1.5529 0.03268 0.02735 -0.0456 0.1811 1.0000
13.750 1.5614 0.03412 0.02880 -0.0447 0.1771 1.0000
14.000 1.5738 0.03528 0.03000 -0.0441 0.1731 1.0000
14.250 1.5838 0.03663 0.03137 -0.0433 0.1689 1.0000
14.500 1.5888 0.03844 0.03317 -0.0424 0.1635 1.0000
14.750 1.5985 0.03984 0.03460 -0.0417 0.1585 1.0000
15.000 1.6011 0.04191 0.03665 -0.0407 0.1513 1.0000
15.250 1.6072 0.04369 0.03843 -0.0400 0.1454 1.0000
15.500 1.6075 0.04603 0.04075 -0.0391 0.1380 1.0000
15.750 1.6076 0.04840 0.04311 -0.0382 0.1303 1.0000
16.000 1.6082 0.05076 0.04547 -0.0375 0.1239 1.0000
16.250 1.6057 0.05349 0.04818 -0.0367 0.1170 1.0000
16.500 1.6068 0.05589 0.05060 -0.0361 0.1117 1.0000
16.750 1.6053 0.05855 0.05325 -0.0355 0.1059 1.0000
17.000 1.6055 0.06112 0.05584 -0.0350 0.1003 1.0000
17.250 1.6027 0.06400 0.05871 -0.0346 0.0938 1.0000
17.500 1.5976 0.06718 0.06187 -0.0342 0.0850 1.0000
17.750 1.5837 0.07135 0.06598 -0.0337 0.0719 1.0000
18.000 1.5773 0.07477 0.06939 -0.0335 0.0662 1.0000
18.250 1.5721 0.07815 0.07280 -0.0334 0.0629 1.0000
18.500 1.5691 0.08129 0.07598 -0.0334 0.0604 1.0000
18.750 1.5682 0.08421 0.07894 -0.0334 0.0590 1.0000
19.000 1.5635 0.08763 0.08242 -0.0336 0.0571 1.0000
19.250 1.5603 0.09090 0.08573 -0.0338 0.0556 1.0000
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Polar data table (+)
Polar graphs
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