GOE 612 AIRFOIL (goe612-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: GOE 612 AIRFOIL (goe612-il) Reynolds number: 200,000 Max Cl/Cd: 74.73 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe612-il-200000.txt Download as CSV file: xf-goe612-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.1415 0.09088 0.08725 -0.0819 0.9682 0.0936
-9.000 -0.1219 0.08826 0.08463 -0.0836 0.9614 0.0958
-8.750 -0.1822 0.03864 0.03487 -0.1247 0.9283 0.0727
-8.500 -0.1439 0.03828 0.03458 -0.1250 0.9253 0.0737
-8.250 -0.3014 0.03418 0.02854 -0.1266 0.9093 0.0644
-8.000 -0.2902 0.03185 0.02586 -0.1251 0.9001 0.0644
-7.750 -0.2693 0.02981 0.02359 -0.1249 0.8939 0.0648
-7.500 -0.2401 0.02835 0.02201 -0.1256 0.8905 0.0659
-7.250 -0.2256 0.02734 0.02087 -0.1236 0.8805 0.0668
-7.000 -0.1998 0.02591 0.01921 -0.1235 0.8756 0.0679
-6.750 -0.1759 0.02454 0.01759 -0.1229 0.8702 0.0689
-6.500 -0.1564 0.02349 0.01632 -0.1215 0.8619 0.0698
-6.250 -0.1286 0.02237 0.01494 -0.1213 0.8577 0.0710
-6.000 -0.1047 0.02136 0.01378 -0.1206 0.8518 0.0722
-5.750 -0.0814 0.02060 0.01306 -0.1198 0.8448 0.0741
-5.500 -0.0524 0.01995 0.01235 -0.1198 0.8405 0.0768
-5.250 -0.0265 0.01939 0.01167 -0.1192 0.8350 0.0795
-5.000 -0.0037 0.01874 0.01098 -0.1182 0.8282 0.0820
-4.750 0.0244 0.01815 0.01042 -0.1180 0.8238 0.0854
-4.500 0.0533 0.01769 0.00985 -0.1179 0.8197 0.0903
-4.250 0.0736 0.01730 0.00955 -0.1165 0.8122 0.0955
-4.000 0.1011 0.01686 0.00906 -0.1162 0.8075 0.1039
-3.750 0.1305 0.01636 0.00855 -0.1163 0.8040 0.1161
-3.500 0.1501 0.01602 0.00833 -0.1148 0.7971 0.1322
-3.250 0.1752 0.01562 0.00802 -0.1142 0.7918 0.1546
-3.000 0.2050 0.01525 0.00766 -0.1143 0.7875 0.1790
-2.750 0.2277 0.01509 0.00761 -0.1133 0.7808 0.2009
-2.500 0.2539 0.01487 0.00742 -0.1127 0.7742 0.2277
-2.250 0.2846 0.01456 0.00717 -0.1129 0.7694 0.2614
-2.000 0.3061 0.01454 0.00727 -0.1116 0.7621 0.2927
-1.750 0.3329 0.01443 0.00720 -0.1112 0.7560 0.3257
-1.500 0.3642 0.01432 0.00705 -0.1114 0.7511 0.3597
-1.250 0.3845 0.01435 0.00718 -0.1098 0.7429 0.3842
-1.000 0.4131 0.01423 0.00704 -0.1096 0.7367 0.4088
-0.750 0.4403 0.01419 0.00699 -0.1092 0.7311 0.4306
-0.500 0.4636 0.01419 0.00703 -0.1081 0.7243 0.4505
-0.250 0.4918 0.01407 0.00693 -0.1079 0.7190 0.4721
0.000 0.5190 0.01399 0.00690 -0.1076 0.7138 0.4954
0.250 0.5411 0.01396 0.00698 -0.1063 0.7070 0.5205
0.500 0.5683 0.01378 0.00688 -0.1059 0.7012 0.5517
0.750 0.5934 0.01358 0.00685 -0.1051 0.6954 0.5977
1.000 0.6122 0.01305 0.00699 -0.1029 0.6882 0.7464
1.250 0.7345 0.01266 0.00672 -0.1218 0.6813 1.0000
1.500 0.7550 0.01280 0.00681 -0.1202 0.6735 1.0000
1.750 0.7796 0.01284 0.00675 -0.1194 0.6659 1.0000
2.000 0.8036 0.01293 0.00675 -0.1184 0.6587 1.0000
2.250 0.8255 0.01301 0.00679 -0.1171 0.6502 1.0000
2.500 0.8513 0.01305 0.00672 -0.1164 0.6426 1.0000
2.750 0.8713 0.01312 0.00678 -0.1146 0.6325 1.0000
3.000 0.8953 0.01317 0.00674 -0.1136 0.6237 1.0000
3.250 0.9160 0.01322 0.00676 -0.1120 0.6130 1.0000
3.500 0.9368 0.01329 0.00678 -0.1104 0.6017 1.0000
3.750 0.9593 0.01332 0.00672 -0.1091 0.5900 1.0000
4.000 0.9780 0.01339 0.00675 -0.1071 0.5759 1.0000
4.250 0.9959 0.01348 0.00679 -0.1049 0.5599 1.0000
4.500 1.0133 0.01360 0.00683 -0.1027 0.5418 1.0000
4.750 1.0290 0.01377 0.00690 -0.1002 0.5212 1.0000
5.000 1.0426 0.01400 0.00704 -0.0973 0.4977 1.0000
5.250 1.0554 0.01433 0.00719 -0.0944 0.4745 1.0000
5.500 1.0674 0.01474 0.00743 -0.0914 0.4527 1.0000
5.750 1.0796 0.01518 0.00772 -0.0885 0.4334 1.0000
6.000 1.0910 0.01565 0.00805 -0.0855 0.4172 1.0000
6.250 1.1032 0.01615 0.00839 -0.0827 0.4036 1.0000
6.500 1.1166 0.01660 0.00879 -0.0802 0.3913 1.0000
6.750 1.1318 0.01709 0.00920 -0.0780 0.3809 1.0000
7.000 1.1480 0.01761 0.00962 -0.0761 0.3717 1.0000
7.250 1.1646 0.01808 0.01008 -0.0743 0.3631 1.0000
7.500 1.1819 0.01862 0.01052 -0.0727 0.3549 1.0000
7.750 1.1988 0.01912 0.01102 -0.0711 0.3472 1.0000
8.000 1.2154 0.01963 0.01149 -0.0694 0.3397 1.0000
8.250 1.2338 0.02019 0.01201 -0.0681 0.3326 1.0000
8.500 1.2489 0.02070 0.01256 -0.0662 0.3256 1.0000
8.750 1.2700 0.02131 0.01304 -0.0654 0.3189 1.0000
9.000 1.2834 0.02184 0.01367 -0.0634 0.3125 1.0000
9.250 1.2986 0.02241 0.01425 -0.0617 0.3061 1.0000
9.500 1.3185 0.02304 0.01481 -0.0608 0.2998 1.0000
9.750 1.3297 0.02365 0.01552 -0.0586 0.2934 1.0000
10.000 1.3446 0.02428 0.01613 -0.0570 0.2871 1.0000
10.250 1.3592 0.02498 0.01685 -0.0554 0.2808 1.0000
10.500 1.3696 0.02568 0.01762 -0.0533 0.2742 1.0000
10.750 1.3862 0.02639 0.01823 -0.0521 0.2679 1.0000
11.000 1.3941 0.02722 0.01921 -0.0499 0.2617 1.0000
11.250 1.4045 0.02803 0.02005 -0.0481 0.2556 1.0000
11.500 1.4197 0.02884 0.02080 -0.0468 0.2497 1.0000
11.750 1.4267 0.02982 0.02191 -0.0448 0.2435 1.0000
12.000 1.4376 0.03072 0.02281 -0.0432 0.2379 1.0000
12.250 1.4499 0.03170 0.02381 -0.0418 0.2323 1.0000
12.500 1.4578 0.03279 0.02500 -0.0401 0.2266 1.0000
12.750 1.4692 0.03377 0.02595 -0.0388 0.2216 1.0000
13.000 1.4799 0.03489 0.02711 -0.0375 0.2165 1.0000
13.250 1.4869 0.03614 0.02847 -0.0360 0.2114 1.0000
13.500 1.4965 0.03726 0.02959 -0.0347 0.2069 1.0000
13.750 1.5080 0.03841 0.03073 -0.0337 0.2023 1.0000
14.000 1.5126 0.03990 0.03236 -0.0323 0.1979 1.0000
14.250 1.5192 0.04128 0.03378 -0.0311 0.1935 1.0000
14.500 1.5355 0.04217 0.03455 -0.0303 0.1892 1.0000
14.750 1.5365 0.04403 0.03662 -0.0290 0.1858 1.0000
15.000 1.5414 0.04568 0.03838 -0.0280 0.1821 1.0000
15.250 1.5484 0.04719 0.03992 -0.0271 0.1785 1.0000
15.500 1.5648 0.04807 0.04070 -0.0265 0.1748 1.0000
15.750 1.5643 0.05027 0.04312 -0.0255 0.1721 1.0000
16.000 1.5674 0.05225 0.04524 -0.0247 0.1691 1.0000
16.250 1.5724 0.05408 0.04714 -0.0241 0.1661 1.0000
16.500 1.5793 0.05569 0.04875 -0.0235 0.1629 1.0000
16.750 1.5890 0.05719 0.05027 -0.0229 0.1599 1.0000
17.000 1.5864 0.05987 0.05316 -0.0224 0.1576 1.0000
17.250 1.5859 0.06240 0.05583 -0.0221 0.1548 1.0000
17.500 1.5875 0.06472 0.05824 -0.0218 0.1519 1.0000
17.750 1.5936 0.06653 0.06003 -0.0216 0.1488 1.0000
18.000 1.5957 0.06891 0.06248 -0.0214 0.1460 1.0000
18.250 1.5861 0.07272 0.06652 -0.0216 0.1434 1.0000
18.500 1.5812 0.07606 0.07001 -0.0220 0.1404 1.0000
18.750 1.5794 0.07904 0.07304 -0.0223 0.1374 1.0000
19.000 1.5845 0.08107 0.07502 -0.0224 0.1337 1.0000
19.250 1.5692 0.08609 0.08029 -0.0236 0.1312 1.0000
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