NACA 6412 (naca6412-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 6412 (naca6412-il) Reynolds number: 100,000 Max Cl/Cd: 58.68 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca6412-il-100000-n5.txt Download as CSV file: xf-naca6412-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 6412
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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.2236 0.09620 0.09112 -0.0677 0.9710 0.0459
-8.500 -0.2154 0.09280 0.08773 -0.0697 0.9635 0.0455
-8.250 -0.2029 0.08860 0.08351 -0.0739 0.9585 0.0451
-8.000 -0.1990 0.08491 0.07984 -0.0764 0.9496 0.0449
-7.750 -0.1884 0.07934 0.07425 -0.0833 0.9428 0.0454
-7.500 -0.1866 0.07360 0.06850 -0.0894 0.9312 0.0459
-7.250 -0.1754 0.06601 0.06083 -0.0989 0.9231 0.0462
-7.000 -0.1643 0.05789 0.05258 -0.1078 0.9136 0.0462
-6.750 -0.1576 0.04610 0.04034 -0.1182 0.9033 0.0466
-6.500 -0.1270 0.04635 0.04063 -0.1189 0.8983 0.0479
-6.250 -0.0987 0.03921 0.03291 -0.1262 0.8941 0.0504
-6.000 -0.0866 0.03339 0.02624 -0.1280 0.8835 0.0523
-5.750 -0.0557 0.02982 0.02200 -0.1304 0.8794 0.0543
-5.500 -0.0312 0.02908 0.02121 -0.1302 0.8721 0.0565
-5.250 -0.0031 0.02757 0.01935 -0.1308 0.8660 0.0598
-5.000 0.0304 0.02573 0.01708 -0.1322 0.8623 0.0631
-4.750 0.0537 0.02513 0.01645 -0.1316 0.8542 0.0659
-4.250 0.1184 0.02314 0.01406 -0.1333 0.8448 0.0750
-4.000 0.1406 0.02268 0.01349 -0.1322 0.8355 0.0798
-3.750 0.1728 0.02187 0.01253 -0.1329 0.8303 0.0857
-3.500 0.2007 0.02140 0.01199 -0.1328 0.8233 0.0923
-3.250 0.2288 0.02083 0.01134 -0.1327 0.8159 0.0991
-3.000 0.2631 0.02024 0.01064 -0.1337 0.8112 0.1083
-2.750 0.2859 0.01991 0.01031 -0.1327 0.8011 0.1153
-2.500 0.3187 0.01940 0.00970 -0.1333 0.7955 0.1264
-2.250 0.3434 0.01917 0.00949 -0.1327 0.7860 0.1374
-2.000 0.3749 0.01874 0.00905 -0.1331 0.7793 0.1502
-1.750 0.4007 0.01851 0.00881 -0.1326 0.7700 0.1638
-1.500 0.4315 0.01818 0.00845 -0.1328 0.7626 0.1804
-1.250 0.4575 0.01801 0.00829 -0.1324 0.7531 0.1977
-1.000 0.4884 0.01773 0.00801 -0.1327 0.7454 0.2188
-0.750 0.5143 0.01761 0.00791 -0.1322 0.7353 0.2405
-0.500 0.5448 0.01737 0.00766 -0.1325 0.7278 0.2672
-0.250 0.5702 0.01729 0.00763 -0.1319 0.7175 0.2955
0.000 0.6018 0.01705 0.00740 -0.1325 0.7100 0.3338
0.250 0.6271 0.01691 0.00742 -0.1320 0.6994 0.3837
0.500 0.6551 0.01630 0.00738 -0.1320 0.6914 0.5607
0.750 0.6956 0.01559 0.00732 -0.1340 0.6816 0.9999
1.000 0.7237 0.01571 0.00726 -0.1339 0.6731 0.9999
1.250 0.7501 0.01588 0.00728 -0.1335 0.6637 0.9999
1.500 0.7772 0.01605 0.00730 -0.1333 0.6552 0.9999
1.750 0.8038 0.01623 0.00737 -0.1330 0.6465 0.9999
2.000 0.8305 0.01643 0.00746 -0.1327 0.6384 0.9999
2.250 0.8566 0.01664 0.00758 -0.1323 0.6300 0.9999
2.500 0.8835 0.01685 0.00770 -0.1321 0.6224 0.9999
2.750 0.9087 0.01710 0.00789 -0.1316 0.6142 0.9999
3.000 0.9364 0.01732 0.00800 -0.1315 0.6076 0.9999
3.250 0.9604 0.01761 0.00829 -0.1308 0.5993 0.9999
3.500 0.9880 0.01784 0.00843 -0.1307 0.5929 0.9999
3.750 1.0118 0.01816 0.00875 -0.1300 0.5852 0.9999
4.000 1.0377 0.01843 0.00899 -0.1297 0.5783 0.9999
4.250 1.0635 0.01873 0.00926 -0.1293 0.5719 0.9999
4.500 1.0873 0.01907 0.00962 -0.1287 0.5646 0.9999
4.750 1.1146 0.01934 0.00985 -0.1286 0.5589 0.9999
5.000 1.1371 0.01972 0.01029 -0.1277 0.5518 0.9999
5.250 1.1619 0.02005 0.01062 -0.1272 0.5452 0.9999
5.500 1.1877 0.02038 0.01094 -0.1269 0.5393 0.9999
5.750 1.2094 0.02079 0.01144 -0.1260 0.5320 0.9999
6.000 1.2353 0.02110 0.01176 -0.1256 0.5261 0.9999
6.250 1.2574 0.02153 0.01226 -0.1248 0.5193 0.9999
6.500 1.2801 0.02192 0.01272 -0.1239 0.5124 0.9999
6.750 1.3057 0.02225 0.01305 -0.1236 0.5064 0.9999
7.000 1.3247 0.02274 0.01368 -0.1222 0.4989 0.9999
7.250 1.3492 0.02309 0.01408 -0.1217 0.4924 0.9999
7.500 1.3684 0.02357 0.01467 -0.1203 0.4847 0.9999
7.750 1.3896 0.02395 0.01511 -0.1193 0.4767 0.9999
8.000 1.4083 0.02439 0.01567 -0.1178 0.4683 0.9999
8.250 1.4274 0.02476 0.01609 -0.1163 0.4589 0.9999
8.500 1.4408 0.02523 0.01667 -0.1140 0.4476 0.9999
8.750 1.4549 0.02561 0.01710 -0.1117 0.4356 0.9999
9.000 1.4671 0.02599 0.01751 -0.1090 0.4229 0.9999
9.250 1.4729 0.02659 0.01823 -0.1055 0.4095 0.9999
9.500 1.4799 0.02725 0.01898 -0.1024 0.3961 0.9999
9.750 1.4869 0.02797 0.01978 -0.0993 0.3822 0.9999
10.000 1.4931 0.02879 0.02068 -0.0963 0.3678 0.9999
10.250 1.4979 0.02976 0.02171 -0.0934 0.3521 0.9999
10.500 1.5015 0.03088 0.02288 -0.0904 0.3350 0.9999
10.750 1.5034 0.03220 0.02420 -0.0875 0.3163 0.9999
11.000 1.5029 0.03377 0.02574 -0.0845 0.2963 0.9999
11.250 1.5010 0.03561 0.02757 -0.0817 0.2744 0.9999
11.500 1.4960 0.03782 0.02972 -0.0790 0.2518 0.9999
11.750 1.4894 0.04034 0.03218 -0.0764 0.2292 0.9999
12.000 1.4805 0.04324 0.03501 -0.0741 0.2071 0.9999
12.250 1.4704 0.04645 0.03816 -0.0720 0.1864 0.9999
12.500 1.4596 0.04994 0.04160 -0.0703 0.1671 0.9999
12.750 1.4484 0.05368 0.04529 -0.0689 0.1502 0.9999
13.000 1.4377 0.05757 0.04916 -0.0679 0.1354 0.9999
13.250 1.4275 0.06156 0.05315 -0.0671 0.1225 0.9999
13.500 1.4181 0.06561 0.05721 -0.0665 0.1116 0.9999
13.750 1.4088 0.06978 0.06139 -0.0661 0.1025 0.9999
14.000 1.4004 0.07392 0.06556 -0.0659 0.0945 0.9999
14.250 1.3937 0.07791 0.06962 -0.0658 0.0874 0.9999
14.500 1.3853 0.08221 0.07393 -0.0659 0.0817 0.9999
14.750 1.3812 0.08599 0.07779 -0.0659 0.0760 0.9999
15.000 1.3748 0.09012 0.08196 -0.0662 0.0716 0.9999
15.250 1.3711 0.09387 0.08578 -0.0663 0.0673 0.9999
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Polar data table (+)
Polar graphs
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