GOE 367 AIRFOIL (goe367-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 367 AIRFOIL (goe367-il) Reynolds number: 200,000 Max Cl/Cd: 67.99 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe367-il-200000.txt Download as CSV file: xf-goe367-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 367 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.1760 0.09710 0.09336 -0.0846 0.9714 0.0872
-9.750 -0.1571 0.09337 0.08961 -0.0887 0.9689 0.0896
-9.500 -0.2049 0.08118 0.07742 -0.1110 0.9545 0.0949
-9.250 -0.1673 0.08018 0.07643 -0.1062 0.9537 0.0957
-9.000 -0.1484 0.07834 0.07458 -0.1048 0.9462 0.0966
-8.750 -0.1324 0.07569 0.07191 -0.1058 0.9397 0.0981
-8.500 -0.1288 0.07260 0.06881 -0.1074 0.9297 0.1000
-8.250 -0.1450 0.06753 0.06369 -0.1124 0.9180 0.1033
-8.000 -0.2869 0.04357 0.03822 -0.1130 0.8953 0.0752
-7.750 -0.2704 0.04095 0.03550 -0.1123 0.8898 0.0743
-7.500 -0.2574 0.03774 0.03205 -0.1113 0.8858 0.0735
-7.250 -0.2528 0.03498 0.02900 -0.1086 0.8768 0.0728
-7.000 -0.2406 0.03187 0.02545 -0.1068 0.8716 0.0728
-6.750 -0.2228 0.02930 0.02239 -0.1054 0.8680 0.0737
-6.500 -0.2097 0.02776 0.02049 -0.1032 0.8596 0.0745
-6.250 -0.1878 0.02602 0.01842 -0.1022 0.8548 0.0753
-6.000 -0.1608 0.02468 0.01700 -0.1022 0.8513 0.0766
-5.750 -0.1392 0.02403 0.01629 -0.1012 0.8447 0.0779
-5.500 -0.1142 0.02335 0.01552 -0.1007 0.8390 0.0798
-5.250 -0.0866 0.02250 0.01449 -0.1004 0.8349 0.0822
-5.000 -0.0605 0.02179 0.01353 -0.0999 0.8301 0.0843
-4.750 -0.0369 0.02102 0.01282 -0.0992 0.8232 0.0864
-4.500 -0.0089 0.02047 0.01224 -0.0991 0.8184 0.0891
-4.250 0.0211 0.01992 0.01154 -0.0992 0.8147 0.0928
-4.000 0.0431 0.01948 0.01110 -0.0982 0.8069 0.0962
-3.750 0.0705 0.01906 0.01071 -0.0979 0.8014 0.1003
-3.500 0.1007 0.01860 0.01011 -0.0980 0.7972 0.1055
-3.250 0.1231 0.01824 0.00984 -0.0971 0.7893 0.1109
-3.000 0.1507 0.01794 0.00947 -0.0968 0.7833 0.1187
-2.750 0.1804 0.01737 0.00893 -0.0969 0.7788 0.1284
-2.500 0.2020 0.01706 0.00869 -0.0957 0.7697 0.1399
-2.250 0.2299 0.01659 0.00821 -0.0955 0.7635 0.1548
-2.000 0.2553 0.01636 0.00796 -0.0949 0.7560 0.1684
-1.750 0.2805 0.01598 0.00764 -0.0943 0.7484 0.1818
-1.500 0.3095 0.01558 0.00723 -0.0944 0.7430 0.1953
-1.250 0.3313 0.01540 0.00714 -0.0933 0.7339 0.2082
-1.000 0.3587 0.01507 0.00683 -0.0931 0.7275 0.2257
-0.750 0.3820 0.01479 0.00671 -0.0922 0.7196 0.2540
-0.500 0.3993 0.01378 0.00653 -0.0905 0.7120 0.4544
-0.250 0.4258 0.01313 0.00725 -0.0875 0.7063 0.9113
0.000 0.4929 0.01361 0.00763 -0.0942 0.6971 0.9563
0.250 0.5779 0.01370 0.00747 -0.1053 0.6901 0.9802
0.500 0.6688 0.01351 0.00718 -0.1184 0.6790 1.0000
0.750 0.6936 0.01346 0.00698 -0.1179 0.6715 1.0000
1.000 0.7155 0.01349 0.00698 -0.1170 0.6610 1.0000
1.250 0.7399 0.01349 0.00685 -0.1164 0.6531 1.0000
1.500 0.7619 0.01353 0.00686 -0.1154 0.6429 1.0000
1.750 0.7856 0.01356 0.00679 -0.1147 0.6345 1.0000
2.000 0.8077 0.01362 0.00681 -0.1137 0.6245 1.0000
2.250 0.8306 0.01369 0.00680 -0.1129 0.6156 1.0000
2.500 0.8528 0.01377 0.00681 -0.1119 0.6060 1.0000
2.750 0.8746 0.01388 0.00687 -0.1109 0.5965 1.0000
3.000 0.8971 0.01398 0.00686 -0.1099 0.5874 1.0000
3.250 0.9174 0.01413 0.00700 -0.1086 0.5774 1.0000
3.500 0.9403 0.01428 0.00702 -0.1078 0.5690 1.0000
3.750 0.9591 0.01448 0.00722 -0.1062 0.5592 1.0000
4.000 0.9822 0.01467 0.00728 -0.1054 0.5511 1.0000
4.250 0.9992 0.01488 0.00752 -0.1035 0.5411 1.0000
4.500 1.0202 0.01510 0.00763 -0.1023 0.5322 1.0000
4.750 1.0365 0.01531 0.00783 -0.1002 0.5221 1.0000
5.000 1.0555 0.01555 0.00801 -0.0986 0.5132 1.0000
5.250 1.0717 0.01578 0.00822 -0.0965 0.5042 1.0000
5.500 1.0911 0.01605 0.00842 -0.0951 0.4967 1.0000
5.750 1.1062 0.01629 0.00870 -0.0928 0.4890 1.0000
6.000 1.1272 0.01658 0.00888 -0.0916 0.4827 1.0000
6.250 1.1414 0.01685 0.00921 -0.0892 0.4759 1.0000
6.500 1.1578 0.01711 0.00947 -0.0872 0.4696 1.0000
6.750 1.1811 0.01743 0.00970 -0.0866 0.4644 1.0000
7.000 1.1930 0.01771 0.01007 -0.0837 0.4585 1.0000
7.250 1.2089 0.01797 0.01034 -0.0817 0.4526 1.0000
7.500 1.2317 0.01828 0.01056 -0.0809 0.4470 1.0000
7.750 1.2428 0.01856 0.01096 -0.0780 0.4410 1.0000
8.000 1.2601 0.01885 0.01126 -0.0763 0.4354 1.0000
8.250 1.2847 0.01918 0.01153 -0.0760 0.4307 1.0000
8.500 1.3000 0.01955 0.01200 -0.0740 0.4260 1.0000
8.750 1.3165 0.01988 0.01240 -0.0723 0.4208 1.0000
9.000 1.3369 0.02020 0.01271 -0.0712 0.4159 1.0000
9.250 1.3577 0.02058 0.01311 -0.0703 0.4112 1.0000
9.500 1.3695 0.02096 0.01361 -0.0678 0.4063 1.0000
9.750 1.3856 0.02132 0.01401 -0.0661 0.4015 1.0000
10.000 1.4104 0.02167 0.01430 -0.0659 0.3965 1.0000
10.250 1.4175 0.02215 0.01494 -0.0628 0.3914 1.0000
10.500 1.4306 0.02260 0.01548 -0.0607 0.3863 1.0000
10.750 1.4497 0.02296 0.01579 -0.0597 0.3803 1.0000
11.000 1.4553 0.02357 0.01655 -0.0566 0.3740 1.0000
11.250 1.4635 0.02413 0.01717 -0.0541 0.3668 1.0000
11.500 1.4728 0.02476 0.01783 -0.0518 0.3593 1.0000
11.750 1.4775 0.02555 0.01872 -0.0491 0.3515 1.0000
12.000 1.4869 0.02630 0.01948 -0.0472 0.3438 1.0000
12.250 1.4901 0.02733 0.02064 -0.0446 0.3354 1.0000
12.500 1.4967 0.02831 0.02166 -0.0426 0.3270 1.0000
12.750 1.4996 0.02956 0.02301 -0.0404 0.3176 1.0000
13.000 1.5025 0.03092 0.02445 -0.0384 0.3076 1.0000
13.250 1.5031 0.03248 0.02604 -0.0363 0.2962 1.0000
13.500 1.5007 0.03440 0.02804 -0.0343 0.2822 1.0000
13.750 1.4961 0.03668 0.03038 -0.0324 0.2638 1.0000
14.000 1.4855 0.03961 0.03329 -0.0304 0.2368 1.0000
14.250 1.4644 0.04370 0.03720 -0.0283 0.2024 1.0000
14.500 1.4392 0.04848 0.04182 -0.0264 0.1809 1.0000
14.750 1.4174 0.05324 0.04649 -0.0250 0.1667 1.0000
15.000 1.4004 0.05773 0.05095 -0.0241 0.1545 1.0000
15.250 1.3874 0.06194 0.05518 -0.0235 0.1434 1.0000
15.500 1.3758 0.06613 0.05938 -0.0231 0.1336 1.0000
15.750 1.3650 0.07035 0.06360 -0.0230 0.1246 1.0000
16.000 1.3588 0.07412 0.06740 -0.0230 0.1162 1.0000
16.250 1.3502 0.07821 0.07150 -0.0231 0.1098 1.0000
16.500 1.3427 0.08223 0.07552 -0.0233 0.1040 1.0000
16.750 1.3349 0.08627 0.07955 -0.0235 0.0992 1.0000
17.000 1.3292 0.09004 0.08334 -0.0238 0.0945 1.0000
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Polar data table (+)
Polar graphs
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