NACA 4412 (naca4412-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 4412 (naca4412-il) Reynolds number: 500,000 Max Cl/Cd: 107.47 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca4412-il-500000.txt Download as CSV file: xf-naca4412-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.8284 0.04176 0.03861 -0.0832 1.0000 0.0246
-12.000 -0.8522 0.03908 0.03574 -0.0799 1.0000 0.0247
-11.750 -0.8699 0.03540 0.03185 -0.0776 0.9997 0.0251
-11.500 -0.8415 0.03435 0.03082 -0.0796 0.9977 0.0258
-11.250 -0.8114 0.03347 0.02989 -0.0818 0.9957 0.0265
-11.000 -0.7822 0.03202 0.02830 -0.0843 0.9939 0.0275
-10.750 -0.7591 0.02982 0.02579 -0.0862 0.9905 0.0285
-10.500 -0.7309 0.02822 0.02384 -0.0882 0.9877 0.0293
-10.250 -0.7053 0.02556 0.02100 -0.0903 0.9856 0.0304
-10.000 -0.6714 0.02497 0.02039 -0.0924 0.9843 0.0314
-9.750 -0.6435 0.02420 0.01952 -0.0932 0.9807 0.0325
-9.500 -0.6134 0.02311 0.01823 -0.0945 0.9778 0.0336
-9.250 -0.5802 0.02227 0.01716 -0.0962 0.9758 0.0345
-9.000 -0.5492 0.02031 0.01504 -0.0982 0.9742 0.0359
-8.750 -0.5132 0.01962 0.01432 -0.1004 0.9731 0.0371
-8.500 -0.4849 0.01894 0.01355 -0.1008 0.9683 0.0381
-8.250 -0.4502 0.01823 0.01273 -0.1025 0.9656 0.0394
-8.000 -0.4135 0.01756 0.01192 -0.1045 0.9637 0.0405
-7.750 -0.3794 0.01639 0.01059 -0.1062 0.9619 0.0416
-7.500 -0.3455 0.01547 0.00965 -0.1078 0.9602 0.0430
-7.250 -0.3201 0.01501 0.00917 -0.1073 0.9539 0.0442
-7.000 -0.2893 0.01445 0.00854 -0.1080 0.9502 0.0454
-6.750 -0.2573 0.01389 0.00791 -0.1088 0.9471 0.0467
-6.500 -0.2303 0.01351 0.00746 -0.1085 0.9415 0.0478
-6.250 -0.2035 0.01278 0.00668 -0.1083 0.9357 0.0494
-6.000 -0.1743 0.01225 0.00613 -0.1085 0.9314 0.0512
-5.750 -0.1485 0.01190 0.00577 -0.1080 0.9242 0.0529
-5.500 -0.1206 0.01155 0.00536 -0.1078 0.9180 0.0550
-5.250 -0.0931 0.01118 0.00493 -0.1076 0.9117 0.0575
-5.000 -0.0666 0.01079 0.00457 -0.1072 0.9038 0.0614
-4.750 -0.0382 0.01055 0.00427 -0.1071 0.8974 0.0656
-4.500 -0.0118 0.01018 0.00393 -0.1067 0.8884 0.0727
-4.250 0.0161 0.00990 0.00363 -0.1066 0.8810 0.0812
-4.000 0.0434 0.00973 0.00343 -0.1063 0.8716 0.0897
-3.750 0.0710 0.00948 0.00321 -0.1061 0.8628 0.1006
-3.500 0.0987 0.00929 0.00301 -0.1060 0.8534 0.1110
-3.250 0.1262 0.00913 0.00285 -0.1058 0.8432 0.1221
-3.000 0.1541 0.00898 0.00269 -0.1056 0.8335 0.1353
-2.750 0.1815 0.00882 0.00255 -0.1054 0.8224 0.1520
-2.500 0.2090 0.00867 0.00244 -0.1053 0.8113 0.1733
-2.250 0.2366 0.00855 0.00235 -0.1051 0.8004 0.1993
-2.000 0.2641 0.00844 0.00229 -0.1049 0.7887 0.2300
-1.750 0.2915 0.00833 0.00224 -0.1048 0.7765 0.2579
-1.500 0.3190 0.00826 0.00218 -0.1046 0.7645 0.2832
-1.250 0.3463 0.00818 0.00213 -0.1044 0.7525 0.3117
-1.000 0.3734 0.00807 0.00209 -0.1042 0.7397 0.3503
-0.750 0.4003 0.00792 0.00208 -0.1040 0.7267 0.4055
-0.500 0.4265 0.00766 0.00208 -0.1038 0.7141 0.5024
-0.250 0.4513 0.00733 0.00214 -0.1031 0.7014 0.6445
0.000 0.4741 0.00703 0.00220 -0.1018 0.6886 0.7752
0.250 0.4944 0.00681 0.00229 -0.0995 0.6757 0.9086
0.500 0.5429 0.00683 0.00228 -0.1037 0.6616 0.9948
0.750 0.5727 0.00693 0.00228 -0.1041 0.6484 1.0000
1.000 0.5983 0.00705 0.00231 -0.1035 0.6356 1.0000
1.250 0.6239 0.00719 0.00235 -0.1030 0.6230 1.0000
1.500 0.6499 0.00731 0.00240 -0.1026 0.6104 1.0000
1.750 0.6761 0.00744 0.00246 -0.1022 0.5984 1.0000
2.000 0.7023 0.00759 0.00253 -0.1018 0.5871 1.0000
2.250 0.7283 0.00775 0.00260 -0.1014 0.5758 1.0000
2.500 0.7548 0.00788 0.00269 -0.1011 0.5646 1.0000
2.750 0.7811 0.00804 0.00279 -0.1007 0.5544 1.0000
3.000 0.8073 0.00820 0.00290 -0.1004 0.5444 1.0000
3.250 0.8339 0.00834 0.00302 -0.1001 0.5349 1.0000
3.500 0.8600 0.00854 0.00314 -0.0998 0.5260 1.0000
3.750 0.8867 0.00866 0.00327 -0.0995 0.5166 1.0000
4.000 0.9127 0.00884 0.00341 -0.0992 0.5067 1.0000
4.250 0.9385 0.00902 0.00355 -0.0988 0.4957 1.0000
4.500 0.9647 0.00917 0.00370 -0.0984 0.4849 1.0000
4.750 0.9903 0.00937 0.00385 -0.0980 0.4741 1.0000
5.000 1.0155 0.00957 0.00400 -0.0975 0.4618 1.0000
5.250 1.0403 0.00977 0.00416 -0.0970 0.4460 1.0000
5.500 1.0652 0.00997 0.00433 -0.0964 0.4309 1.0000
5.750 1.0906 0.01016 0.00452 -0.0960 0.4187 1.0000
6.000 1.1155 0.01038 0.00472 -0.0955 0.4067 1.0000
6.250 1.1399 0.01063 0.00495 -0.0949 0.3935 1.0000
6.500 1.1639 0.01090 0.00518 -0.0942 0.3784 1.0000
6.750 1.1875 0.01119 0.00543 -0.0935 0.3609 1.0000
7.000 1.2103 0.01152 0.00571 -0.0927 0.3410 1.0000
7.250 1.2318 0.01193 0.00603 -0.0917 0.3191 1.0000
7.500 1.2528 0.01238 0.00639 -0.0906 0.2935 1.0000
7.750 1.2718 0.01294 0.00682 -0.0892 0.2643 1.0000
8.000 1.2891 0.01362 0.00734 -0.0876 0.2320 1.0000
8.250 1.3042 0.01442 0.00794 -0.0856 0.1973 1.0000
8.500 1.3175 0.01531 0.00862 -0.0834 0.1607 1.0000
8.750 1.3282 0.01622 0.00934 -0.0807 0.1301 1.0000
9.000 1.3388 0.01711 0.01011 -0.0781 0.1080 1.0000
9.250 1.3500 0.01798 0.01089 -0.0756 0.0904 1.0000
9.500 1.3615 0.01884 0.01169 -0.0732 0.0782 1.0000
9.750 1.3735 0.01968 0.01251 -0.0709 0.0704 1.0000
10.000 1.3845 0.02060 0.01340 -0.0687 0.0648 1.0000
10.250 1.3969 0.02144 0.01429 -0.0667 0.0610 1.0000
10.500 1.4094 0.02230 0.01519 -0.0648 0.0580 1.0000
10.750 1.4184 0.02340 0.01630 -0.0626 0.0550 1.0000
11.000 1.4270 0.02457 0.01753 -0.0605 0.0528 1.0000
11.250 1.4395 0.02551 0.01855 -0.0589 0.0510 1.0000
11.500 1.4503 0.02659 0.01969 -0.0573 0.0492 1.0000
11.750 1.4584 0.02791 0.02104 -0.0555 0.0473 1.0000
12.000 1.4602 0.02976 0.02294 -0.0533 0.0455 1.0000
12.250 1.4688 0.03116 0.02443 -0.0519 0.0443 1.0000
12.500 1.4791 0.03246 0.02581 -0.0507 0.0429 1.0000
12.750 1.4875 0.03395 0.02738 -0.0495 0.0414 1.0000
13.000 1.4938 0.03568 0.02917 -0.0483 0.0400 1.0000
13.250 1.4941 0.03801 0.03154 -0.0469 0.0387 1.0000
13.500 1.4941 0.04045 0.03407 -0.0457 0.0375 1.0000
13.750 1.5030 0.04212 0.03584 -0.0450 0.0363 1.0000
14.000 1.5091 0.04410 0.03790 -0.0444 0.0349 1.0000
14.250 1.5135 0.04630 0.04017 -0.0438 0.0337 1.0000
14.500 1.5126 0.04913 0.04305 -0.0432 0.0326 1.0000
14.750 1.5064 0.05260 0.04659 -0.0426 0.0315 1.0000
15.000 1.5124 0.05486 0.04898 -0.0424 0.0305 1.0000
15.250 1.5153 0.05748 0.05169 -0.0423 0.0294 1.0000
15.500 1.5171 0.06031 0.05459 -0.0423 0.0283 1.0000
15.750 1.5155 0.06359 0.05793 -0.0425 0.0274 1.0000
16.000 1.5055 0.06789 0.06228 -0.0426 0.0265 1.0000
16.250 1.5080 0.07082 0.06534 -0.0429 0.0257 1.0000
16.500 1.5081 0.07407 0.06871 -0.0433 0.0248 1.0000
16.750 1.5068 0.07756 0.07229 -0.0439 0.0240 1.0000
17.000 1.5043 0.08125 0.07605 -0.0445 0.0233 1.0000
17.250 1.4987 0.08538 0.08024 -0.0453 0.0226 1.0000
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