GOE 612 AIRFOIL (goe612-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 612 AIRFOIL (goe612-il) Reynolds number: 200,000 Max Cl/Cd: 70.08 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe612-il-200000-n5.txt Download as CSV file: xf-goe612-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 612 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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.4703 0.04222 0.03733 -0.1276 0.9567 0.0391
-11.000 -0.4792 0.03849 0.03330 -0.1300 0.9444 0.0393
-10.750 -0.4773 0.03595 0.03052 -0.1304 0.9346 0.0396
-10.500 -0.4670 0.03378 0.02809 -0.1308 0.9271 0.0400
-10.250 -0.4602 0.03216 0.02627 -0.1294 0.9173 0.0404
-10.000 -0.4453 0.03053 0.02439 -0.1290 0.9105 0.0410
-9.750 -0.4351 0.02915 0.02278 -0.1274 0.9009 0.0415
-9.500 -0.4180 0.02772 0.02108 -0.1266 0.8939 0.0421
-9.250 -0.4034 0.02655 0.01967 -0.1251 0.8847 0.0426
-9.000 -0.3836 0.02541 0.01829 -0.1243 0.8776 0.0430
-8.750 -0.3638 0.02440 0.01724 -0.1234 0.8699 0.0434
-8.500 -0.3425 0.02354 0.01633 -0.1226 0.8622 0.0439
-8.250 -0.3196 0.02274 0.01543 -0.1220 0.8554 0.0445
-8.000 -0.2984 0.02202 0.01463 -0.1210 0.8465 0.0451
-7.750 -0.2738 0.02126 0.01376 -0.1205 0.8400 0.0458
-7.500 -0.2523 0.02062 0.01302 -0.1195 0.8308 0.0466
-7.250 -0.2274 0.01997 0.01222 -0.1190 0.8243 0.0476
-7.000 -0.2043 0.01943 0.01155 -0.1182 0.8160 0.0486
-6.750 -0.1802 0.01878 0.01085 -0.1176 0.8088 0.0496
-6.500 -0.1564 0.01824 0.01028 -0.1169 0.8014 0.0506
-6.250 -0.1320 0.01776 0.00974 -0.1163 0.7938 0.0517
-6.000 -0.1066 0.01729 0.00918 -0.1158 0.7876 0.0530
-5.750 -0.0825 0.01689 0.00870 -0.1150 0.7803 0.0544
-5.500 -0.0571 0.01647 0.00820 -0.1145 0.7743 0.0558
-5.250 -0.0323 0.01607 0.00778 -0.1140 0.7683 0.0579
-5.000 -0.0074 0.01576 0.00742 -0.1133 0.7616 0.0606
-4.750 0.0187 0.01544 0.00702 -0.1129 0.7561 0.0636
-4.500 0.0441 0.01514 0.00671 -0.1124 0.7507 0.0673
-4.250 0.0694 0.01488 0.00643 -0.1118 0.7450 0.0721
-4.000 0.0957 0.01464 0.00618 -0.1114 0.7399 0.0790
-3.750 0.1226 0.01444 0.00595 -0.1111 0.7352 0.0894
-3.500 0.1479 0.01428 0.00581 -0.1106 0.7296 0.1018
-3.250 0.1740 0.01410 0.00564 -0.1102 0.7246 0.1147
-3.000 0.2012 0.01392 0.00543 -0.1099 0.7195 0.1277
-2.750 0.2263 0.01377 0.00532 -0.1093 0.7129 0.1415
-2.500 0.2519 0.01362 0.00519 -0.1088 0.7062 0.1578
-2.000 0.3035 0.01334 0.00502 -0.1078 0.6941 0.2038
-1.750 0.3291 0.01322 0.00497 -0.1072 0.6877 0.2336
-1.250 0.3803 0.01306 0.00495 -0.1061 0.6752 0.2964
-1.000 0.4062 0.01302 0.00491 -0.1055 0.6683 0.3201
-0.750 0.4323 0.01299 0.00487 -0.1050 0.6618 0.3383
-0.500 0.4571 0.01296 0.00488 -0.1043 0.6546 0.3550
-0.250 0.4834 0.01295 0.00486 -0.1038 0.6489 0.3723
0.000 0.5092 0.01294 0.00487 -0.1032 0.6434 0.3904
0.250 0.5341 0.01293 0.00491 -0.1025 0.6373 0.4079
0.500 0.5599 0.01292 0.00490 -0.1020 0.6313 0.4258
0.750 0.5850 0.01290 0.00493 -0.1013 0.6251 0.4456
1.000 0.6090 0.01287 0.00498 -0.1004 0.6178 0.4712
1.250 0.6337 0.01281 0.00498 -0.0996 0.6114 0.5034
1.500 0.6563 0.01272 0.00506 -0.0985 0.6041 0.5406
1.750 0.6784 0.01256 0.00509 -0.0972 0.5964 0.5969
2.250 0.7994 0.01210 0.00534 -0.1103 0.5750 1.0000
2.500 0.8206 0.01223 0.00543 -0.1089 0.5647 1.0000
2.750 0.8416 0.01236 0.00548 -0.1075 0.5536 1.0000
3.000 0.8618 0.01251 0.00554 -0.1058 0.5408 1.0000
3.250 0.8813 0.01267 0.00563 -0.1041 0.5258 1.0000
3.500 0.8999 0.01286 0.00573 -0.1022 0.5092 1.0000
3.750 0.9173 0.01309 0.00583 -0.1001 0.4904 1.0000
4.000 0.9333 0.01335 0.00598 -0.0978 0.4692 1.0000
4.250 0.9475 0.01368 0.00616 -0.0951 0.4467 1.0000
4.500 0.9601 0.01406 0.00638 -0.0923 0.4256 1.0000
4.750 0.9719 0.01447 0.00665 -0.0893 0.4068 1.0000
5.000 0.9826 0.01488 0.00694 -0.0861 0.3907 1.0000
5.250 0.9940 0.01530 0.00726 -0.0831 0.3768 1.0000
5.500 1.0064 0.01573 0.00760 -0.0804 0.3650 1.0000
5.750 1.0183 0.01622 0.00799 -0.0777 0.3540 1.0000
6.000 1.0328 0.01666 0.00837 -0.0755 0.3433 1.0000
6.250 1.0464 0.01716 0.00879 -0.0732 0.3341 1.0000
6.500 1.0617 0.01763 0.00922 -0.0713 0.3253 1.0000
6.750 1.0760 0.01815 0.00968 -0.0693 0.3181 1.0000
7.000 1.0932 0.01858 0.01011 -0.0677 0.3113 1.0000
7.250 1.1088 0.01909 0.01058 -0.0660 0.3053 1.0000
7.500 1.1246 0.01961 0.01108 -0.0643 0.3001 1.0000
7.750 1.1423 0.02006 0.01155 -0.0629 0.2946 1.0000
8.000 1.1581 0.02060 0.01208 -0.0613 0.2891 1.0000
8.250 1.1727 0.02121 0.01265 -0.0596 0.2841 1.0000
8.500 1.1902 0.02170 0.01320 -0.0584 0.2785 1.0000
8.750 1.2059 0.02228 0.01379 -0.0569 0.2731 1.0000
9.000 1.2195 0.02297 0.01445 -0.0552 0.2679 1.0000
9.250 1.2358 0.02354 0.01509 -0.0540 0.2626 1.0000
9.500 1.2509 0.02419 0.01576 -0.0526 0.2570 1.0000
9.750 1.2640 0.02495 0.01651 -0.0510 0.2520 1.0000
10.000 1.2789 0.02564 0.01725 -0.0497 0.2471 1.0000
10.250 1.2932 0.02638 0.01805 -0.0484 0.2415 1.0000
10.500 1.3054 0.02725 0.01891 -0.0470 0.2364 1.0000
10.750 1.3185 0.02810 0.01980 -0.0457 0.2315 1.0000
11.000 1.3318 0.02895 0.02071 -0.0444 0.2258 1.0000
11.250 1.3425 0.02998 0.02175 -0.0430 0.2206 1.0000
11.500 1.3542 0.03097 0.02279 -0.0418 0.2154 1.0000
11.750 1.3657 0.03201 0.02388 -0.0406 0.2096 1.0000
12.000 1.3744 0.03325 0.02512 -0.0393 0.2044 1.0000
12.250 1.3854 0.03438 0.02631 -0.0382 0.1993 1.0000
12.500 1.3956 0.03560 0.02758 -0.0371 0.1943 1.0000
12.750 1.4033 0.03701 0.02901 -0.0359 0.1898 1.0000
13.000 1.4130 0.03832 0.03037 -0.0349 0.1856 1.0000
13.250 1.4224 0.03968 0.03180 -0.0340 0.1811 1.0000
13.500 1.4296 0.04124 0.03339 -0.0330 0.1769 1.0000
13.750 1.4358 0.04291 0.03507 -0.0320 0.1730 1.0000
14.000 1.4449 0.04439 0.03664 -0.0313 0.1688 1.0000
14.250 1.4509 0.04616 0.03846 -0.0305 0.1642 1.0000
14.500 1.4544 0.04816 0.04047 -0.0297 0.1604 1.0000
14.750 1.4619 0.04987 0.04227 -0.0290 0.1564 1.0000
15.000 1.4674 0.05180 0.04428 -0.0285 0.1524 1.0000
15.250 1.4712 0.05392 0.04643 -0.0279 0.1491 1.0000
15.500 1.4738 0.05618 0.04869 -0.0274 0.1461 1.0000
15.750 1.4808 0.05806 0.05071 -0.0270 0.1435 1.0000
16.000 1.4858 0.06016 0.05292 -0.0267 0.1406 1.0000
16.250 1.4882 0.06260 0.05542 -0.0264 0.1374 1.0000
16.500 1.4898 0.06513 0.05800 -0.0263 0.1349 1.0000
16.750 1.4912 0.06772 0.06063 -0.0261 0.1324 1.0000
17.000 1.4945 0.07021 0.06327 -0.0261 0.1296 1.0000
17.250 1.4962 0.07289 0.06607 -0.0262 0.1270 1.0000
17.500 1.4965 0.07578 0.06905 -0.0264 0.1246 1.0000
17.750 1.4947 0.07897 0.07229 -0.0267 0.1221 1.0000
18.000 1.4932 0.08214 0.07551 -0.0271 0.1199 1.0000
18.250 1.4919 0.08545 0.07899 -0.0277 0.1170 1.0000
18.500 1.4891 0.08898 0.08266 -0.0284 0.1143 1.0000
18.750 1.4853 0.09267 0.08644 -0.0292 0.1119 1.0000
19.000 1.4801 0.09661 0.09045 -0.0303 0.1095 1.0000
19.250 1.4744 0.10069 0.09463 -0.0314 0.1069 1.0000
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