GOE 508 AIRFOIL (goe508-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 508 AIRFOIL (goe508-il) Reynolds number: 1,000,000 Max Cl/Cd: 115.88 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe508-il-1000000-n5.txt Download as CSV file: xf-goe508-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.000 -0.7336 0.05365 0.05065 -0.1201 0.9460 0.0242
-15.750 -0.7515 0.03595 0.03244 -0.1472 0.9278 0.0243
-15.500 -0.7378 0.03076 0.02690 -0.1570 0.8890 0.0244
-15.250 -0.7463 0.02825 0.02412 -0.1573 0.8559 0.0245
-15.000 -0.7551 0.02644 0.02212 -0.1557 0.8361 0.0245
-14.750 -0.7591 0.02512 0.02066 -0.1534 0.8223 0.0245
-14.500 -0.7601 0.02410 0.01948 -0.1507 0.8100 0.0246
-14.250 -0.7600 0.02314 0.01842 -0.1478 0.7997 0.0247
-14.000 -0.7557 0.02244 0.01760 -0.1448 0.7905 0.0248
-13.750 -0.7499 0.02178 0.01684 -0.1418 0.7828 0.0249
-13.500 -0.7438 0.02122 0.01619 -0.1387 0.7760 0.0250
-13.250 -0.7344 0.02058 0.01546 -0.1362 0.7705 0.0250
-13.000 -0.7188 0.02008 0.01487 -0.1345 0.7655 0.0251
-12.750 -0.7063 0.01939 0.01410 -0.1324 0.7599 0.0253
-12.250 -0.6755 0.01817 0.01273 -0.1290 0.7501 0.0256
-12.000 -0.6572 0.01765 0.01216 -0.1276 0.7451 0.0258
-11.750 -0.6378 0.01719 0.01164 -0.1263 0.7405 0.0260
-11.250 -0.5964 0.01635 0.01068 -0.1241 0.7319 0.0263
-11.000 -0.5746 0.01596 0.01024 -0.1231 0.7268 0.0265
-10.750 -0.5526 0.01560 0.00981 -0.1221 0.7218 0.0267
-10.500 -0.5302 0.01526 0.00941 -0.1211 0.7172 0.0269
-10.250 -0.5070 0.01491 0.00901 -0.1203 0.7134 0.0271
-10.000 -0.4836 0.01457 0.00862 -0.1195 0.7090 0.0273
-9.750 -0.4601 0.01425 0.00825 -0.1187 0.7043 0.0275
-9.250 -0.4121 0.01366 0.00754 -0.1173 0.6951 0.0280
-9.000 -0.3877 0.01338 0.00721 -0.1166 0.6897 0.0282
-8.750 -0.3632 0.01312 0.00690 -0.1159 0.6846 0.0284
-8.500 -0.3385 0.01288 0.00659 -0.1152 0.6802 0.0286
-8.250 -0.3131 0.01262 0.00630 -0.1147 0.6758 0.0288
-8.000 -0.2888 0.01231 0.00595 -0.1140 0.6708 0.0292
-7.750 -0.2639 0.01207 0.00567 -0.1133 0.6656 0.0296
-7.500 -0.2385 0.01185 0.00542 -0.1128 0.6610 0.0299
-7.250 -0.2126 0.01164 0.00519 -0.1123 0.6555 0.0303
-7.000 -0.1870 0.01147 0.00498 -0.1117 0.6494 0.0308
-6.750 -0.1613 0.01131 0.00478 -0.1112 0.6440 0.0313
-6.500 -0.1351 0.01113 0.00457 -0.1108 0.6386 0.0317
-6.250 -0.1091 0.01098 0.00437 -0.1103 0.6329 0.0321
-6.000 -0.0833 0.01084 0.00419 -0.1097 0.6275 0.0325
-5.750 -0.0570 0.01066 0.00399 -0.1093 0.6223 0.0330
-5.500 -0.0311 0.01050 0.00381 -0.1088 0.6164 0.0337
-5.250 -0.0054 0.01038 0.00366 -0.1083 0.6106 0.0344
-5.000 0.0213 0.01025 0.00352 -0.1079 0.6050 0.0352
-4.750 0.0475 0.01015 0.00338 -0.1074 0.5986 0.0359
-4.500 0.0735 0.01007 0.00326 -0.1069 0.5927 0.0367
-4.250 0.1000 0.00995 0.00313 -0.1065 0.5875 0.0376
-4.000 0.1263 0.00985 0.00301 -0.1061 0.5821 0.0387
-3.750 0.1523 0.00978 0.00292 -0.1056 0.5768 0.0401
-3.500 0.1790 0.00971 0.00283 -0.1052 0.5719 0.0414
-3.250 0.2051 0.00963 0.00274 -0.1047 0.5652 0.0429
-3.000 0.2304 0.00959 0.00267 -0.1041 0.5574 0.0446
-2.750 0.2569 0.00953 0.00259 -0.1037 0.5513 0.0463
-2.500 0.2831 0.00947 0.00252 -0.1033 0.5462 0.0481
-2.250 0.3089 0.00942 0.00246 -0.1027 0.5419 0.0505
-2.000 0.3355 0.00938 0.00241 -0.1024 0.5385 0.0527
-1.750 0.3618 0.00930 0.00235 -0.1020 0.5344 0.0565
-1.500 0.3875 0.00925 0.00230 -0.1014 0.5289 0.0621
-1.000 0.4384 0.00914 0.00227 -0.1003 0.5189 0.0878
-0.750 0.4647 0.00911 0.00226 -0.0999 0.5153 0.0960
-0.500 0.4908 0.00911 0.00226 -0.0995 0.5113 0.1022
-0.250 0.5161 0.00911 0.00226 -0.0989 0.5072 0.1085
0.000 0.5421 0.00910 0.00227 -0.0985 0.5034 0.1145
0.250 0.5682 0.00908 0.00227 -0.0980 0.4996 0.1216
0.500 0.5939 0.00908 0.00228 -0.0975 0.4954 0.1298
0.750 0.6187 0.00908 0.00231 -0.0969 0.4909 0.1413
1.000 0.6432 0.00907 0.00234 -0.0962 0.4868 0.1599
1.250 0.6683 0.00901 0.00236 -0.0956 0.4823 0.1870
1.500 0.6926 0.00899 0.00240 -0.0949 0.4771 0.2168
1.750 0.7150 0.00897 0.00246 -0.0938 0.4710 0.2566
2.000 0.7381 0.00886 0.00252 -0.0929 0.4657 0.3202
2.250 0.7594 0.00872 0.00259 -0.0917 0.4599 0.4055
2.500 0.7783 0.00857 0.00268 -0.0899 0.4541 0.5073
2.750 0.7981 0.00841 0.00276 -0.0884 0.4495 0.6010
3.000 0.8155 0.00826 0.00285 -0.0862 0.4437 0.6940
3.250 0.8276 0.00813 0.00295 -0.0829 0.4377 0.7826
3.500 0.8446 0.00797 0.00311 -0.0804 0.4322 0.8937
4.000 1.0055 0.00873 0.00378 -0.1036 0.4013 0.9933
4.250 1.0568 0.00912 0.00404 -0.1090 0.3805 1.0000
4.500 1.0648 0.00944 0.00425 -0.1051 0.3605 1.0000
4.750 1.0643 0.00983 0.00451 -0.0996 0.3373 1.0000
5.000 1.0621 0.01024 0.00479 -0.0938 0.3131 1.0000
5.250 1.0647 0.01071 0.00513 -0.0890 0.2918 1.0000
5.500 1.0709 0.01119 0.00551 -0.0852 0.2730 1.0000
5.750 1.0808 0.01164 0.00588 -0.0821 0.2587 1.0000
6.000 1.0955 0.01199 0.00619 -0.0799 0.2510 1.0000
6.250 1.1096 0.01239 0.00655 -0.0777 0.2435 1.0000
6.500 1.1249 0.01278 0.00691 -0.0758 0.2371 1.0000
6.750 1.1409 0.01317 0.00728 -0.0741 0.2318 1.0000
7.000 1.1545 0.01370 0.00776 -0.0721 0.2244 1.0000
7.250 1.1722 0.01408 0.00814 -0.0707 0.2218 1.0000
7.500 1.1899 0.01448 0.00854 -0.0694 0.2187 1.0000
7.750 1.2070 0.01493 0.00899 -0.0681 0.2157 1.0000
8.000 1.2230 0.01546 0.00951 -0.0667 0.2121 1.0000
8.250 1.2383 0.01604 0.01007 -0.0653 0.2082 1.0000
8.500 1.2552 0.01657 0.01061 -0.0641 0.2058 1.0000
8.750 1.2733 0.01706 0.01112 -0.0632 0.2036 1.0000
9.000 1.2907 0.01760 0.01168 -0.0622 0.2020 1.0000
9.250 1.3071 0.01821 0.01229 -0.0611 0.1992 1.0000
9.500 1.3231 0.01887 0.01296 -0.0600 0.1970 1.0000
9.750 1.3384 0.01958 0.01367 -0.0590 0.1946 1.0000
10.000 1.3527 0.02037 0.01448 -0.0578 0.1920 1.0000
10.250 1.3687 0.02107 0.01520 -0.0569 0.1902 1.0000
10.500 1.3850 0.02177 0.01593 -0.0560 0.1887 1.0000
10.750 1.4010 0.02249 0.01668 -0.0552 0.1868 1.0000
11.000 1.4147 0.02337 0.01757 -0.0542 0.1831 1.0000
11.250 1.4264 0.02441 0.01859 -0.0530 0.1786 1.0000
11.500 1.4388 0.02542 0.01962 -0.0520 0.1749 1.0000
11.750 1.4518 0.02640 0.02060 -0.0511 0.1698 1.0000
12.000 1.4594 0.02778 0.02196 -0.0498 0.1627 1.0000
12.250 1.4705 0.02895 0.02313 -0.0488 0.1568 1.0000
12.500 1.4746 0.03066 0.02478 -0.0474 0.1460 1.0000
12.750 1.4798 0.03233 0.02643 -0.0462 0.1386 1.0000
13.000 1.4821 0.03425 0.02832 -0.0448 0.1288 1.0000
13.250 1.4854 0.03616 0.03021 -0.0436 0.1211 1.0000
13.500 1.4901 0.03800 0.03205 -0.0426 0.1161 1.0000
13.750 1.4944 0.03989 0.03393 -0.0416 0.1098 1.0000
14.000 1.4998 0.04174 0.03580 -0.0407 0.1060 1.0000
14.250 1.5042 0.04369 0.03775 -0.0399 0.1011 1.0000
14.500 1.5055 0.04596 0.04000 -0.0390 0.0938 1.0000
14.750 1.4998 0.04891 0.04290 -0.0379 0.0797 1.0000
15.000 1.4888 0.05246 0.04637 -0.0367 0.0650 1.0000
15.250 1.4889 0.05500 0.04891 -0.0361 0.0602 1.0000
15.500 1.4927 0.05721 0.05115 -0.0356 0.0581 1.0000
15.750 1.4959 0.05950 0.05347 -0.0352 0.0561 1.0000
16.000 1.4973 0.06202 0.05602 -0.0348 0.0538 1.0000
16.250 1.5017 0.06424 0.05829 -0.0345 0.0528 1.0000
16.500 1.5060 0.06651 0.06061 -0.0343 0.0515 1.0000
16.750 1.5105 0.06874 0.06288 -0.0341 0.0507 1.0000
17.000 1.5119 0.07133 0.06552 -0.0339 0.0492 1.0000
17.250 1.5151 0.07375 0.06798 -0.0338 0.0484 1.0000
17.500 1.5154 0.07655 0.07083 -0.0338 0.0473 1.0000
17.750 1.5186 0.07899 0.07331 -0.0337 0.0459 1.0000
18.000 1.5203 0.08167 0.07605 -0.0338 0.0450 1.0000
18.250 1.5222 0.08428 0.07871 -0.0339 0.0435 1.0000
18.500 1.5215 0.08726 0.08175 -0.0340 0.0424 1.0000
18.750 1.5203 0.09032 0.08484 -0.0342 0.0410 1.0000
19.000 1.5201 0.09331 0.08789 -0.0345 0.0395 1.0000
19.250 1.5170 0.09664 0.09124 -0.0349 0.0364 1.0000
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