GOE 195 AIRFOIL (goe195-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 195 AIRFOIL (goe195-il) Reynolds number: 100,000 Max Cl/Cd: 63.31 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe195-il-100000.txt Download as CSV file: xf-goe195-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 195 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3173 0.10061 0.09561 -0.0295 1.0000 0.0996
-7.750 -0.3345 0.10049 0.09564 -0.0291 1.0000 0.1022
-7.500 -0.3579 0.10106 0.09637 -0.0299 1.0000 0.1031
-7.250 -0.3520 0.09646 0.09180 -0.0272 1.0000 0.1049
-7.000 -0.3382 0.09309 0.08843 -0.0235 1.0000 0.1084
-6.750 -0.3404 0.09123 0.08663 -0.0221 1.0000 0.1116
-6.500 -0.3480 0.08982 0.08532 -0.0224 1.0000 0.1154
-6.250 -0.3580 0.08861 0.08421 -0.0323 1.0000 0.1184
-6.000 -0.3298 0.07875 0.07485 -0.0139 1.0000 0.1210
-5.750 -0.3309 0.07675 0.07289 -0.0118 1.0000 0.1237
-5.500 -0.3356 0.07493 0.07112 -0.0112 1.0000 0.1273
-5.250 -0.3395 0.07765 0.07338 -0.0321 1.0000 0.1336
-5.000 -0.3389 0.07532 0.07110 -0.0266 1.0000 0.1354
-4.750 -0.3339 0.07342 0.06922 -0.0242 1.0000 0.1400
-4.500 -0.3145 0.06987 0.06564 -0.0323 1.0000 0.1496
-4.250 -0.3093 0.06796 0.06377 -0.0291 1.0000 0.1532
-4.000 -0.2347 0.06322 0.05870 -0.0515 0.9943 0.1773
-3.750 -0.2139 0.05928 0.05486 -0.0501 0.9885 0.1798
-3.500 -0.1634 0.05542 0.05086 -0.0591 0.9827 0.1946
-3.250 -0.0349 0.03365 0.02700 -0.0951 0.9851 0.1032
-3.000 0.0145 0.02955 0.02257 -0.1008 0.9816 0.0965
-2.750 0.0678 0.02633 0.01826 -0.1060 0.9768 0.0903
-2.500 0.1169 0.02464 0.01625 -0.1104 0.9720 0.0914
-2.250 0.1597 0.02352 0.01499 -0.1135 0.9640 0.0944
-2.000 0.2086 0.02244 0.01374 -0.1174 0.9579 0.0960
-1.750 0.2494 0.02165 0.01287 -0.1197 0.9482 0.0989
-1.500 0.2990 0.02085 0.01203 -0.1236 0.9422 0.1043
-1.250 0.3375 0.02023 0.01148 -0.1256 0.9309 0.1164
-1.000 0.3819 0.01936 0.01099 -0.1286 0.9219 0.1648
-0.750 0.4284 0.01918 0.01109 -0.1317 0.9133 0.3306
-0.500 0.4649 0.01896 0.01102 -0.1331 0.9012 0.3858
-0.250 0.5022 0.01863 0.01079 -0.1343 0.8898 0.4274
0.000 0.5442 0.01810 0.01034 -0.1362 0.8817 0.4682
0.250 0.5764 0.01774 0.01011 -0.1363 0.8681 0.5133
0.500 0.6088 0.01730 0.00979 -0.1363 0.8547 0.5573
0.750 0.6403 0.01669 0.00941 -0.1363 0.8414 0.6239
1.000 0.6695 0.01561 0.00886 -0.1354 0.8282 1.0000
1.250 0.7017 0.01555 0.00856 -0.1355 0.8148 1.0000
1.500 0.7325 0.01552 0.00837 -0.1354 0.8017 1.0000
1.750 0.7628 0.01551 0.00821 -0.1351 0.7890 1.0000
2.000 0.7913 0.01559 0.00816 -0.1346 0.7752 1.0000
2.250 0.8186 0.01573 0.00819 -0.1339 0.7605 1.0000
2.500 0.8455 0.01589 0.00827 -0.1332 0.7458 1.0000
2.750 0.8721 0.01612 0.00843 -0.1325 0.7316 1.0000
3.000 0.8985 0.01640 0.00866 -0.1318 0.7183 1.0000
3.250 0.9251 0.01669 0.00893 -0.1313 0.7059 1.0000
3.500 0.9524 0.01695 0.00914 -0.1307 0.6946 1.0000
3.750 0.9786 0.01725 0.00943 -0.1301 0.6823 1.0000
4.000 1.0039 0.01758 0.00981 -0.1294 0.6693 1.0000
4.250 1.0294 0.01783 0.01007 -0.1286 0.6556 1.0000
4.500 1.0547 0.01801 0.01025 -0.1276 0.6405 1.0000
4.750 1.0799 0.01813 0.01036 -0.1265 0.6242 1.0000
5.000 1.1051 0.01822 0.01045 -0.1254 0.6070 1.0000
5.250 1.1304 0.01837 0.01056 -0.1243 0.5901 1.0000
5.500 1.1554 0.01861 0.01077 -0.1232 0.5730 1.0000
5.750 1.1788 0.01893 0.01114 -0.1220 0.5535 1.0000
6.000 1.2020 0.01923 0.01142 -0.1207 0.5319 1.0000
6.250 1.2248 0.01956 0.01169 -0.1192 0.5088 1.0000
6.500 1.2457 0.01987 0.01205 -0.1176 0.4840 1.0000
6.750 1.2664 0.02014 0.01241 -0.1160 0.4595 1.0000
7.000 1.2865 0.02038 0.01273 -0.1143 0.4338 1.0000
7.250 1.3048 0.02061 0.01301 -0.1123 0.4016 1.0000
7.500 1.3213 0.02098 0.01335 -0.1101 0.3617 1.0000
7.750 1.3359 0.02170 0.01393 -0.1078 0.3197 1.0000
8.000 1.3478 0.02277 0.01477 -0.1052 0.2738 1.0000
8.250 1.3558 0.02421 0.01592 -0.1023 0.2236 1.0000
8.500 1.3586 0.02616 0.01748 -0.0987 0.1623 1.0000
8.750 1.3554 0.02870 0.01953 -0.0945 0.1216 1.0000
9.000 1.3576 0.03081 0.02151 -0.0908 0.1024 1.0000
9.250 1.3617 0.03271 0.02334 -0.0874 0.0926 1.0000
9.500 1.3691 0.03447 0.02507 -0.0846 0.0852 1.0000
9.750 1.3806 0.03623 0.02690 -0.0823 0.0788 1.0000
10.000 1.3924 0.03790 0.02854 -0.0803 0.0736 1.0000
10.250 1.4127 0.04007 0.03071 -0.0792 0.0696 1.0000
10.500 1.4292 0.04188 0.03272 -0.0775 0.0658 1.0000
10.750 1.4450 0.04372 0.03457 -0.0762 0.0623 1.0000
11.000 1.4737 0.04677 0.03770 -0.0764 0.0595 1.0000
11.250 1.4896 0.04948 0.04076 -0.0749 0.0579 1.0000
11.500 1.4991 0.05218 0.04378 -0.0727 0.0564 1.0000
11.750 1.5048 0.05475 0.04660 -0.0704 0.0547 1.0000
12.000 1.5092 0.05729 0.04935 -0.0681 0.0532 1.0000
12.250 1.5116 0.06030 0.05257 -0.0659 0.0523 1.0000
12.500 1.5097 0.06381 0.05635 -0.0635 0.0519 1.0000
12.750 1.5020 0.06753 0.06037 -0.0609 0.0517 1.0000
13.000 1.4883 0.07146 0.06463 -0.0584 0.0517 1.0000
13.250 1.4690 0.07576 0.06927 -0.0564 0.0520 1.0000
13.500 1.4441 0.08072 0.07459 -0.0552 0.0524 1.0000
13.750 1.4073 0.08704 0.08131 -0.0555 0.0530 1.0000
14.000 1.3689 0.09464 0.08928 -0.0577 0.0538 1.0000
14.250 1.3300 0.10345 0.09837 -0.0618 0.0547 1.0000
14.500 1.2895 0.11380 0.10898 -0.0680 0.0558 1.0000
14.750 1.2479 0.12613 0.12151 -0.0762 0.0571 1.0000
15.000 1.2115 0.13945 0.13492 -0.0851 0.0586 1.0000
15.250 1.1912 0.15019 0.14569 -0.0914 0.0598 1.0000
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Polar data table (+)
Polar graphs
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