NACA 4412 (naca4412-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 4412 (naca4412-il) Reynolds number: 1,000,000 Max Cl/Cd: 119.16 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca4412-il-1000000-n5.txt Download as CSV file: xf-naca4412-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 4412
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.250 -0.7721 0.10360 0.10134 -0.0468 1.0000 0.0136
-16.000 -0.8530 0.08592 0.08350 -0.0576 1.0000 0.0134
-15.750 -1.1564 0.03236 0.02901 -0.1001 1.0000 0.0112
-15.500 -1.1690 0.03033 0.02686 -0.0971 1.0000 0.0113
-15.250 -1.1706 0.02854 0.02496 -0.0951 0.9996 0.0115
-15.000 -1.1512 0.02673 0.02302 -0.0965 0.9977 0.0119
-14.750 -1.1291 0.02527 0.02146 -0.0977 0.9959 0.0123
-14.500 -1.1047 0.02402 0.02012 -0.0989 0.9946 0.0128
-14.250 -1.0802 0.02294 0.01894 -0.0998 0.9930 0.0132
-14.000 -1.0558 0.02198 0.01787 -0.1004 0.9908 0.0137
-13.750 -1.0298 0.02107 0.01687 -0.1012 0.9889 0.0141
-13.500 -1.0023 0.02021 0.01595 -0.1022 0.9873 0.0148
-13.250 -0.9737 0.01948 0.01517 -0.1032 0.9859 0.0154
-13.000 -0.9447 0.01881 0.01444 -0.1042 0.9845 0.0161
-12.750 -0.9185 0.01820 0.01375 -0.1044 0.9818 0.0167
-12.500 -0.8923 0.01763 0.01310 -0.1047 0.9787 0.0171
-12.250 -0.8652 0.01702 0.01244 -0.1051 0.9760 0.0177
-12.000 -0.8368 0.01652 0.01190 -0.1056 0.9739 0.0183
-11.750 -0.8099 0.01606 0.01140 -0.1058 0.9709 0.0189
-11.500 -0.7843 0.01565 0.01093 -0.1056 0.9668 0.0196
-11.250 -0.7573 0.01525 0.01047 -0.1057 0.9634 0.0202
-11.000 -0.7295 0.01488 0.01002 -0.1059 0.9605 0.0206
-10.750 -0.7045 0.01439 0.00949 -0.1057 0.9559 0.0212
-10.500 -0.6784 0.01399 0.00905 -0.1055 0.9514 0.0218
-10.250 -0.6515 0.01364 0.00866 -0.1055 0.9474 0.0223
-10.000 -0.6249 0.01333 0.00830 -0.1053 0.9431 0.0230
-9.750 -0.5984 0.01302 0.00794 -0.1051 0.9377 0.0236
-9.500 -0.5715 0.01272 0.00757 -0.1050 0.9324 0.0241
-9.250 -0.5448 0.01244 0.00723 -0.1048 0.9258 0.0245
-9.000 -0.5185 0.01210 0.00682 -0.1045 0.9176 0.0250
-8.750 -0.4922 0.01172 0.00639 -0.1043 0.9099 0.0258
-8.500 -0.4653 0.01142 0.00604 -0.1041 0.9023 0.0264
-8.250 -0.4381 0.01116 0.00574 -0.1040 0.8954 0.0271
-8.000 -0.4108 0.01092 0.00545 -0.1039 0.8875 0.0277
-7.750 -0.3835 0.01069 0.00515 -0.1038 0.8801 0.0283
-7.500 -0.3560 0.01047 0.00487 -0.1037 0.8716 0.0289
-7.250 -0.3285 0.01028 0.00461 -0.1035 0.8633 0.0293
-7.000 -0.3012 0.01001 0.00428 -0.1034 0.8540 0.0299
-6.750 -0.2737 0.00976 0.00398 -0.1033 0.8447 0.0308
-6.500 -0.2463 0.00957 0.00374 -0.1032 0.8350 0.0318
-6.250 -0.2185 0.00940 0.00352 -0.1031 0.8244 0.0326
-6.000 -0.1908 0.00924 0.00330 -0.1030 0.8140 0.0334
-5.750 -0.1632 0.00911 0.00310 -0.1029 0.8029 0.0342
-5.500 -0.1353 0.00897 0.00291 -0.1028 0.7914 0.0351
-5.250 -0.1076 0.00882 0.00271 -0.1027 0.7803 0.0368
-5.000 -0.0799 0.00870 0.00255 -0.1026 0.7687 0.0387
-4.750 -0.0520 0.00860 0.00240 -0.1025 0.7567 0.0408
-4.500 -0.0242 0.00847 0.00225 -0.1025 0.7451 0.0445
-4.250 0.0036 0.00839 0.00212 -0.1024 0.7336 0.0484
-4.000 0.0313 0.00829 0.00201 -0.1023 0.7216 0.0545
-3.750 0.0593 0.00820 0.00191 -0.1022 0.7099 0.0607
-3.500 0.0873 0.00814 0.00182 -0.1022 0.6983 0.0662
-3.250 0.1151 0.00808 0.00173 -0.1021 0.6864 0.0729
-3.000 0.1431 0.00804 0.00166 -0.1021 0.6746 0.0783
-2.750 0.1710 0.00798 0.00159 -0.1021 0.6624 0.0859
-2.500 0.1989 0.00795 0.00153 -0.1020 0.6500 0.0927
-2.250 0.2268 0.00792 0.00148 -0.1019 0.6379 0.1013
-2.000 0.2546 0.00789 0.00144 -0.1019 0.6250 0.1115
-1.750 0.2825 0.00786 0.00140 -0.1019 0.6122 0.1239
-1.500 0.3103 0.00781 0.00138 -0.1018 0.6005 0.1437
-1.000 0.3657 0.00774 0.00136 -0.1017 0.5764 0.1875
-0.750 0.3936 0.00773 0.00136 -0.1017 0.5655 0.2056
-0.500 0.4215 0.00773 0.00138 -0.1017 0.5553 0.2251
-0.250 0.4493 0.00774 0.00139 -0.1017 0.5447 0.2425
0.000 0.4773 0.00775 0.00141 -0.1017 0.5354 0.2569
0.250 0.5050 0.00779 0.00144 -0.1016 0.5261 0.2722
0.500 0.5330 0.00777 0.00147 -0.1016 0.5174 0.2949
0.750 0.5606 0.00777 0.00152 -0.1016 0.5089 0.3252
1.000 0.5884 0.00771 0.00156 -0.1016 0.5005 0.3718
1.250 0.6156 0.00757 0.00163 -0.1016 0.4922 0.4581
1.500 0.6427 0.00739 0.00171 -0.1016 0.4835 0.5636
1.750 0.6696 0.00730 0.00180 -0.1014 0.4748 0.6432
2.000 0.6964 0.00721 0.00189 -0.1012 0.4658 0.7162
2.250 0.7219 0.00709 0.00199 -0.1007 0.4583 0.8029
2.500 0.7433 0.00691 0.00211 -0.0990 0.4509 0.9164
2.750 0.7804 0.00695 0.00218 -0.1009 0.4427 1.0000
3.000 0.8076 0.00706 0.00225 -0.1008 0.4347 1.0000
3.250 0.8345 0.00720 0.00235 -0.1006 0.4250 1.0000
3.750 0.8878 0.00751 0.00255 -0.1001 0.4020 1.0000
4.000 0.9142 0.00769 0.00268 -0.0999 0.3885 1.0000
4.250 0.9402 0.00789 0.00281 -0.0995 0.3732 1.0000
4.500 0.9650 0.00818 0.00298 -0.0990 0.3498 1.0000
4.750 0.9889 0.00855 0.00319 -0.0984 0.3188 1.0000
5.000 1.0135 0.00886 0.00339 -0.0979 0.2962 1.0000
5.250 1.0381 0.00917 0.00361 -0.0973 0.2755 1.0000
5.500 1.0622 0.00952 0.00385 -0.0967 0.2548 1.0000
5.750 1.0855 0.00992 0.00412 -0.0960 0.2300 1.0000
6.000 1.1082 0.01035 0.00442 -0.0952 0.2049 1.0000
6.250 1.1306 0.01081 0.00475 -0.0944 0.1809 1.0000
6.500 1.1525 0.01129 0.00510 -0.0935 0.1558 1.0000
6.750 1.1740 0.01178 0.00547 -0.0925 0.1330 1.0000
7.000 1.1957 0.01224 0.00584 -0.0915 0.1156 1.0000
7.250 1.2177 0.01266 0.00620 -0.0906 0.1023 1.0000
7.500 1.2395 0.01308 0.00656 -0.0897 0.0903 1.0000
7.750 1.2602 0.01356 0.00695 -0.0886 0.0772 1.0000
8.000 1.2806 0.01403 0.00737 -0.0875 0.0662 1.0000
8.250 1.3014 0.01445 0.00776 -0.0864 0.0591 1.0000
8.500 1.3213 0.01490 0.00818 -0.0852 0.0533 1.0000
8.750 1.3414 0.01529 0.00856 -0.0839 0.0496 1.0000
9.000 1.3586 0.01575 0.00901 -0.0822 0.0452 1.0000
9.250 1.3771 0.01615 0.00942 -0.0807 0.0427 1.0000
9.500 1.3945 0.01662 0.00989 -0.0791 0.0401 1.0000
9.750 1.4113 0.01713 0.01040 -0.0775 0.0377 1.0000
10.000 1.4293 0.01757 0.01088 -0.0760 0.0366 1.0000
10.250 1.4463 0.01807 0.01140 -0.0745 0.0350 1.0000
10.500 1.4624 0.01864 0.01198 -0.0729 0.0336 1.0000
10.750 1.4774 0.01927 0.01263 -0.0712 0.0320 1.0000
11.000 1.4935 0.01985 0.01325 -0.0697 0.0311 1.0000
11.250 1.5092 0.02046 0.01390 -0.0682 0.0302 1.0000
11.500 1.5239 0.02115 0.01462 -0.0666 0.0290 1.0000
11.750 1.5375 0.02192 0.01541 -0.0650 0.0278 1.0000
12.000 1.5498 0.02280 0.01632 -0.0633 0.0265 1.0000
12.250 1.5637 0.02359 0.01716 -0.0619 0.0258 1.0000
12.500 1.5768 0.02445 0.01808 -0.0605 0.0249 1.0000
12.750 1.5889 0.02542 0.01908 -0.0590 0.0238 1.0000
13.000 1.5993 0.02653 0.02021 -0.0575 0.0225 1.0000
13.250 1.6098 0.02767 0.02140 -0.0560 0.0215 1.0000
13.500 1.6202 0.02886 0.02265 -0.0547 0.0204 1.0000
13.750 1.6291 0.03020 0.02403 -0.0534 0.0192 1.0000
14.000 1.6365 0.03169 0.02555 -0.0520 0.0181 1.0000
14.250 1.6445 0.03320 0.02712 -0.0509 0.0172 1.0000
14.500 1.6510 0.03489 0.02886 -0.0497 0.0162 1.0000
14.750 1.6558 0.03677 0.03078 -0.0486 0.0152 1.0000
15.000 1.6603 0.03873 0.03281 -0.0476 0.0145 1.0000
15.250 1.6646 0.04079 0.03494 -0.0468 0.0138 1.0000
15.500 1.6676 0.04306 0.03727 -0.0460 0.0131 1.0000
15.750 1.6689 0.04554 0.03982 -0.0453 0.0124 1.0000
16.000 1.6696 0.04818 0.04252 -0.0448 0.0119 1.0000
16.250 1.6710 0.05082 0.04525 -0.0444 0.0115 1.0000
16.500 1.6713 0.05366 0.04816 -0.0442 0.0111 1.0000
16.750 1.6702 0.05669 0.05128 -0.0440 0.0107 1.0000
17.000 1.6680 0.05993 0.05460 -0.0440 0.0103 1.0000
17.250 1.6647 0.06338 0.05813 -0.0441 0.0100 1.0000
17.500 1.6603 0.06703 0.06186 -0.0443 0.0097 1.0000
17.750 1.6553 0.07082 0.06574 -0.0447 0.0094 1.0000
18.000 1.6510 0.07455 0.06957 -0.0452 0.0093 1.0000
18.250 1.6459 0.07846 0.07357 -0.0458 0.0091 1.0000
18.500 1.6399 0.08255 0.07776 -0.0465 0.0089 1.0000
18.750 1.6332 0.08679 0.08209 -0.0474 0.0087 1.0000
19.000 1.6254 0.09120 0.08659 -0.0483 0.0085 1.0000
19.250 1.6170 0.09575 0.09125 -0.0494 0.0084 1.0000
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