GOE 650 AIRFOIL (goe650-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 650 AIRFOIL (goe650-il) Reynolds number: 100,000 Max Cl/Cd: 53.93 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe650-il-100000-n5.txt Download as CSV file: xf-goe650-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 650 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.3979 0.10384 0.09818 -0.0494 1.0000 0.0586
-11.000 -0.4107 0.09909 0.09347 -0.0501 1.0000 0.0592
-10.500 -0.7134 0.05498 0.04944 -0.0660 0.9999 0.0583
-10.250 -0.7175 0.04383 0.03773 -0.0833 0.9881 0.0592
-10.000 -0.6997 0.03972 0.03322 -0.0889 0.9817 0.0607
-9.750 -0.6828 0.03653 0.02962 -0.0919 0.9748 0.0626
-9.500 -0.6552 0.03512 0.02816 -0.0942 0.9709 0.0645
-9.250 -0.6342 0.03378 0.02671 -0.0950 0.9646 0.0667
-9.000 -0.6082 0.03199 0.02464 -0.0969 0.9598 0.0699
-8.750 -0.5823 0.03068 0.02321 -0.0982 0.9551 0.0726
-8.500 -0.5584 0.02969 0.02213 -0.0986 0.9491 0.0757
-8.250 -0.5297 0.02843 0.02064 -0.1001 0.9452 0.0809
-8.000 -0.5018 0.02777 0.01995 -0.1010 0.9411 0.0860
-7.750 -0.4796 0.02695 0.01898 -0.1008 0.9349 0.0920
-7.500 -0.4496 0.02636 0.01828 -0.1018 0.9309 0.0992
-7.250 -0.4164 0.02579 0.01761 -0.1034 0.9279 0.1063
-7.000 -0.3954 0.02532 0.01693 -0.1026 0.9212 0.1134
-6.750 -0.3676 0.02502 0.01662 -0.1029 0.9167 0.1196
-6.500 -0.3358 0.02456 0.01590 -0.1040 0.9136 0.1275
-6.250 -0.3018 0.02425 0.01561 -0.1055 0.9112 0.1339
-6.000 -0.2834 0.02404 0.01523 -0.1039 0.9036 0.1409
-5.750 -0.2544 0.02386 0.01505 -0.1044 0.8994 0.1485
-5.500 -0.2214 0.02360 0.01456 -0.1056 0.8965 0.1583
-5.250 -0.1869 0.02322 0.01426 -0.1069 0.8943 0.1647
-5.000 -0.1696 0.02298 0.01393 -0.1050 0.8859 0.1693
-4.750 -0.1368 0.02247 0.01326 -0.1059 0.8815 0.1752
-4.500 -0.0992 0.02194 0.01275 -0.1076 0.8784 0.1808
-4.250 -0.0745 0.02162 0.01236 -0.1069 0.8712 0.1864
-4.000 -0.0454 0.02126 0.01193 -0.1070 0.8658 0.1925
-3.750 -0.0112 0.02090 0.01158 -0.1081 0.8625 0.1993
-3.500 0.0258 0.02052 0.01109 -0.1097 0.8600 0.2075
-3.250 0.0425 0.02043 0.01108 -0.1076 0.8519 0.2131
-3.000 0.0734 0.02018 0.01079 -0.1080 0.8474 0.2227
-2.750 0.1079 0.01987 0.01052 -0.1091 0.8442 0.2323
-2.500 0.1383 0.01965 0.01028 -0.1094 0.8399 0.2434
-2.250 0.1590 0.01961 0.01029 -0.1080 0.8322 0.2538
-2.000 0.1918 0.01937 0.01009 -0.1087 0.8283 0.2676
-1.750 0.2281 0.01909 0.00985 -0.1100 0.8253 0.2837
-1.500 0.2461 0.01916 0.00995 -0.1080 0.8167 0.2976
-1.250 0.2775 0.01900 0.00982 -0.1084 0.8118 0.3153
-1.000 0.3136 0.01877 0.00964 -0.1096 0.8084 0.3343
-0.750 0.3337 0.01886 0.00976 -0.1080 0.8000 0.3503
-0.500 0.3650 0.01873 0.00967 -0.1083 0.7945 0.3688
-0.250 0.4033 0.01845 0.00941 -0.1098 0.7904 0.3882
0.000 0.4234 0.01847 0.00947 -0.1080 0.7795 0.4042
0.250 0.4647 0.01800 0.00901 -0.1098 0.7726 0.4237
0.500 0.4861 0.01793 0.00896 -0.1081 0.7597 0.4395
0.750 0.5152 0.01774 0.00881 -0.1078 0.7497 0.4564
1.000 0.5449 0.01759 0.00869 -0.1076 0.7406 0.4742
1.250 0.5710 0.01754 0.00869 -0.1069 0.7303 0.4922
1.500 0.6038 0.01736 0.00854 -0.1073 0.7211 0.5131
1.750 0.6270 0.01735 0.00861 -0.1061 0.7090 0.5328
2.000 0.6564 0.01721 0.00854 -0.1059 0.6982 0.5549
2.250 0.6837 0.01711 0.00850 -0.1053 0.6860 0.5783
2.500 0.7069 0.01708 0.00857 -0.1041 0.6719 0.6032
2.750 0.7317 0.01699 0.00859 -0.1032 0.6578 0.6336
3.250 0.7820 0.01654 0.00858 -0.1012 0.6266 0.7549
3.500 0.8254 0.01636 0.00854 -0.1040 0.6061 1.0000
3.750 0.8499 0.01648 0.00854 -0.1030 0.5867 1.0000
4.000 0.8747 0.01662 0.00852 -0.1021 0.5665 1.0000
4.250 0.8980 0.01684 0.00858 -0.1009 0.5452 1.0000
4.500 0.9203 0.01712 0.00872 -0.0996 0.5239 1.0000
4.750 0.9415 0.01746 0.00891 -0.0981 0.5021 1.0000
5.000 0.9616 0.01783 0.00915 -0.0965 0.4803 1.0000
5.250 0.9804 0.01824 0.00944 -0.0947 0.4581 1.0000
5.500 0.9977 0.01867 0.00977 -0.0927 0.4348 1.0000
5.750 1.0144 0.01913 0.01011 -0.0906 0.4121 1.0000
6.000 1.0301 0.01962 0.01047 -0.0884 0.3910 1.0000
6.250 1.0450 0.02014 0.01085 -0.0860 0.3719 1.0000
6.500 1.0599 0.02069 0.01128 -0.0837 0.3547 1.0000
7.000 1.0910 0.02185 0.01228 -0.0796 0.3258 1.0000
7.250 1.1071 0.02245 0.01283 -0.0777 0.3133 1.0000
7.500 1.1231 0.02308 0.01339 -0.0758 0.3022 1.0000
7.750 1.1390 0.02372 0.01400 -0.0739 0.2913 1.0000
8.000 1.1553 0.02435 0.01463 -0.0722 0.2812 1.0000
8.250 1.1706 0.02504 0.01527 -0.0703 0.2720 1.0000
8.500 1.1870 0.02568 0.01596 -0.0687 0.2629 1.0000
8.750 1.2018 0.02641 0.01666 -0.0668 0.2548 1.0000
9.000 1.2177 0.02710 0.01740 -0.0652 0.2464 1.0000
9.250 1.2321 0.02787 0.01815 -0.0634 0.2389 1.0000
9.500 1.2473 0.02862 0.01896 -0.0618 0.2315 1.0000
9.750 1.2614 0.02942 0.01980 -0.0600 0.2244 1.0000
10.000 1.2757 0.03027 0.02064 -0.0584 0.2183 1.0000
10.250 1.2897 0.03111 0.02157 -0.0568 0.2114 1.0000
10.500 1.3019 0.03203 0.02247 -0.0550 0.2054 1.0000
10.750 1.3146 0.03296 0.02350 -0.0534 0.1988 1.0000
11.000 1.3254 0.03394 0.02454 -0.0516 0.1925 1.0000
11.250 1.3355 0.03501 0.02561 -0.0498 0.1866 1.0000
11.500 1.3458 0.03608 0.02681 -0.0482 0.1802 1.0000
11.750 1.3546 0.03724 0.02799 -0.0465 0.1751 1.0000
12.000 1.3647 0.03843 0.02928 -0.0450 0.1701 1.0000
12.250 1.3739 0.03968 0.03065 -0.0435 0.1650 1.0000
12.500 1.3817 0.04101 0.03203 -0.0419 0.1608 1.0000
12.750 1.3894 0.04242 0.03351 -0.0405 0.1564 1.0000
13.000 1.3956 0.04395 0.03520 -0.0391 0.1511 1.0000
13.250 1.3998 0.04560 0.03692 -0.0377 0.1466 1.0000
13.500 1.4041 0.04735 0.03876 -0.0365 0.1422 1.0000
13.750 1.4077 0.04924 0.04082 -0.0354 0.1372 1.0000
14.000 1.4089 0.05131 0.04297 -0.0343 0.1328 1.0000
14.250 1.4105 0.05349 0.04525 -0.0334 0.1286 1.0000
14.500 1.4116 0.05585 0.04779 -0.0327 0.1240 1.0000
14.750 1.4100 0.05847 0.05052 -0.0321 0.1198 1.0000
15.000 1.4078 0.06130 0.05346 -0.0317 0.1156 1.0000
15.250 1.4049 0.06441 0.05676 -0.0315 0.1107 1.0000
15.500 1.3990 0.06790 0.06033 -0.0317 0.1065 1.0000
15.750 1.3932 0.07162 0.06421 -0.0320 0.1021 1.0000
16.000 1.3850 0.07583 0.06858 -0.0328 0.0973 1.0000
16.250 1.3741 0.08050 0.07331 -0.0339 0.0935 1.0000
16.500 1.3637 0.08549 0.07852 -0.0353 0.0886 1.0000
16.750 1.3497 0.09109 0.08424 -0.0372 0.0845 1.0000
17.000 1.3351 0.09702 0.09030 -0.0395 0.0807 1.0000
17.250 1.3188 0.10347 0.09691 -0.0422 0.0767 1.0000
17.500 1.3020 0.11011 0.10362 -0.0452 0.0737 1.0000
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