NACA 6412 (naca6412-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 6412 (naca6412-il) Reynolds number: 50,000 Max Cl/Cd: 29.61 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca6412-il-50000-n5.txt Download as CSV file: xf-naca6412-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3155 0.12121 0.11463 -0.0304 1.0001 0.1160
-8.500 -0.3221 0.11963 0.11313 -0.0288 1.0001 0.1184
-8.250 -0.3285 0.11792 0.11150 -0.0281 0.9992 0.1206
-8.000 -0.3281 0.11564 0.10924 -0.0339 0.9915 0.1241
-7.500 -0.3146 0.10334 0.09684 -0.0436 0.9770 0.0819
-7.250 -0.2966 0.09906 0.09254 -0.0472 0.9712 0.0792
-7.000 -0.2865 0.09492 0.08839 -0.0513 0.9620 0.0777
-6.750 -0.2720 0.09050 0.08394 -0.0568 0.9536 0.0778
-6.500 -0.2563 0.08594 0.07935 -0.0625 0.9447 0.0781
-6.250 -0.2424 0.08138 0.07473 -0.0677 0.9354 0.0776
-6.000 -0.2202 0.07576 0.06900 -0.0753 0.9278 0.0766
-5.750 -0.2041 0.07067 0.06379 -0.0807 0.9178 0.0760
-5.500 -0.1743 0.06532 0.05823 -0.0881 0.9113 0.0778
-5.250 -0.1539 0.06030 0.05297 -0.0931 0.9014 0.0796
-5.000 -0.1179 0.05339 0.04554 -0.1016 0.8956 0.0811
-4.750 -0.0901 0.04749 0.03894 -0.1070 0.8872 0.0838
-4.500 -0.0592 0.04642 0.03787 -0.1084 0.8805 0.0876
-4.250 -0.0278 0.04324 0.03420 -0.1113 0.8734 0.0914
-4.000 0.0051 0.04004 0.03029 -0.1141 0.8661 0.0971
-3.750 0.0429 0.03866 0.02876 -0.1164 0.8614 0.1028
-3.500 0.0677 0.03693 0.02642 -0.1167 0.8515 0.1099
-3.250 0.1037 0.03585 0.02530 -0.1184 0.8461 0.1167
-3.000 0.1306 0.03475 0.02375 -0.1186 0.8371 0.1256
-2.750 0.1642 0.03391 0.02289 -0.1197 0.8309 0.1337
-2.500 0.1952 0.03312 0.02184 -0.1204 0.8234 0.1446
-2.250 0.2254 0.03252 0.02102 -0.1208 0.8155 0.1575
-2.000 0.2645 0.03170 0.02013 -0.1225 0.8113 0.1721
-1.750 0.2846 0.03154 0.01993 -0.1213 0.8002 0.1844
-1.500 0.3241 0.03087 0.01913 -0.1230 0.7955 0.2045
-1.250 0.3470 0.03076 0.01896 -0.1222 0.7851 0.2218
-1.000 0.3841 0.03022 0.01832 -0.1235 0.7797 0.2476
-0.750 0.4087 0.03011 0.01824 -0.1230 0.7702 0.2709
-0.500 0.4425 0.02964 0.01778 -0.1238 0.7639 0.3038
-0.250 0.4703 0.02938 0.01761 -0.1238 0.7557 0.3395
0.000 0.5002 0.02895 0.01738 -0.1241 0.7482 0.3905
0.250 0.5357 0.02780 0.01695 -0.1250 0.7442 0.5327
0.500 0.5543 0.02733 0.01715 -0.1229 0.7328 0.9999
0.750 0.5911 0.02720 0.01667 -0.1240 0.7279 0.9999
1.000 0.6096 0.02782 0.01710 -0.1227 0.7171 0.9999
1.250 0.6444 0.02775 0.01680 -0.1234 0.7118 0.9999
1.500 0.6635 0.02837 0.01729 -0.1222 0.7017 0.9999
1.750 0.6960 0.02839 0.01714 -0.1227 0.6959 0.9999
2.000 0.7171 0.02896 0.01761 -0.1218 0.6869 0.9999
2.250 0.7458 0.02917 0.01769 -0.1218 0.6802 0.9999
2.500 0.7741 0.02941 0.01783 -0.1217 0.6738 0.9999
2.750 0.7942 0.03005 0.01842 -0.1207 0.6650 0.9999
3.000 0.8293 0.02997 0.01824 -0.1215 0.6605 0.9999
3.250 0.8417 0.03103 0.01929 -0.1196 0.6502 0.9999
3.500 0.8739 0.03108 0.01928 -0.1200 0.6450 0.9999
3.750 0.8903 0.03199 0.02020 -0.1186 0.6365 0.9999
4.000 0.9165 0.03236 0.02054 -0.1183 0.6299 0.9999
4.250 0.9532 0.03219 0.02033 -0.1192 0.6259 0.9999
4.500 0.9576 0.03376 0.02196 -0.1165 0.6152 0.9999
4.750 0.9916 0.03371 0.02191 -0.1170 0.6105 0.9999
5.000 0.9992 0.03515 0.02341 -0.1147 0.6010 0.9999
5.250 1.0275 0.03543 0.02370 -0.1146 0.5953 0.9999
5.500 1.0497 0.03606 0.02439 -0.1139 0.5889 0.9999
5.750 1.0605 0.03730 0.02570 -0.1119 0.5803 0.9999
6.000 1.0979 0.03708 0.02551 -0.1128 0.5761 0.9999
6.250 1.0918 0.03929 0.02781 -0.1090 0.5654 0.9999
6.500 1.1254 0.03923 0.02783 -0.1095 0.5605 0.9999
6.750 1.1240 0.04126 0.02996 -0.1063 0.5507 0.9999
7.000 1.1501 0.04160 0.03038 -0.1059 0.5447 0.9999
7.500 1.1732 0.04417 0.03317 -0.1025 0.5287 0.9999
7.750 1.2179 0.04323 0.03233 -0.1036 0.5249 0.9999
8.000 1.1947 0.04692 0.03613 -0.0990 0.5122 0.9999
8.250 1.2389 0.04582 0.03517 -0.0998 0.5084 0.9999
8.500 1.2140 0.04988 0.03935 -0.0957 0.4954 0.9999
8.750 1.2611 0.04830 0.03791 -0.0963 0.4915 0.9999
9.000 1.2345 0.05269 0.04240 -0.0924 0.4779 0.9999
9.250 1.2540 0.05321 0.04306 -0.0912 0.4704 0.9999
9.500 1.2573 0.05516 0.04513 -0.0893 0.4600 0.9999
10.000 1.2860 0.05679 0.04707 -0.0863 0.4418 0.9999
10.250 1.2636 0.06147 0.05185 -0.0840 0.4276 0.9999
10.500 1.2559 0.06476 0.05526 -0.0823 0.4149 0.9999
10.750 1.3054 0.06102 0.05172 -0.0809 0.4084 0.9999
11.000 1.2890 0.06512 0.05594 -0.0791 0.3940 0.9999
11.250 1.2824 0.06819 0.05912 -0.0777 0.3801 0.9999
11.500 1.2867 0.06979 0.06085 -0.0762 0.3670 0.9999
11.750 1.3038 0.06950 0.06070 -0.0744 0.3542 0.9999
12.000 1.3175 0.06962 0.06096 -0.0728 0.3401 0.9999
12.250 1.3215 0.07116 0.06261 -0.0714 0.3247 0.9999
12.500 1.3214 0.07337 0.06493 -0.0702 0.3084 0.9999
12.750 1.3200 0.07587 0.06752 -0.0693 0.2911 0.9999
13.000 1.3209 0.07811 0.06983 -0.0683 0.2729 0.9999
13.250 1.3254 0.07978 0.07152 -0.0672 0.2534 0.9999
13.500 1.3309 0.08128 0.07295 -0.0660 0.2328 0.9999
13.750 1.3259 0.08468 0.07635 -0.0656 0.2128 0.9999
14.000 1.3230 0.08775 0.07932 -0.0651 0.1935 0.9999
14.250 1.3190 0.09105 0.08248 -0.0647 0.1761 0.9999
14.500 1.3136 0.09468 0.08599 -0.0645 0.1607 0.9999
14.750 1.3081 0.09854 0.08977 -0.0646 0.1472 0.9999
15.000 1.3033 0.10242 0.09362 -0.0648 0.1353 0.9999
15.250 1.2998 0.10615 0.09732 -0.0650 0.1250 0.9999
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Polar data table (+)
Polar graphs
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