NACA 4412 (naca4412-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 4412 (naca4412-il) Reynolds number: 1,000,000 Max Cl/Cd: 129.37 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca4412-il-1000000.txt Download as CSV file: xf-naca4412-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.750 -0.8374 0.08373 0.08141 -0.0585 1.0000 0.0169
-15.500 -0.9127 0.06837 0.06591 -0.0687 1.0000 0.0166
-15.250 -1.0965 0.03328 0.03022 -0.0993 1.0000 0.0153
-15.000 -1.1161 0.03120 0.02803 -0.0956 1.0000 0.0154
-14.750 -1.1210 0.02977 0.02651 -0.0926 1.0000 0.0156
-14.500 -1.1215 0.02857 0.02523 -0.0896 1.0000 0.0159
-14.250 -1.1181 0.02751 0.02407 -0.0870 1.0000 0.0162
-14.000 -1.0990 0.02637 0.02282 -0.0871 0.9992 0.0166
-13.750 -1.0711 0.02533 0.02165 -0.0885 0.9979 0.0170
-13.500 -1.0462 0.02365 0.01985 -0.0903 0.9963 0.0177
-13.250 -1.0163 0.02288 0.01905 -0.0918 0.9951 0.0183
-13.000 -0.9847 0.02237 0.01850 -0.0933 0.9943 0.0189
-12.750 -0.9549 0.02183 0.01790 -0.0943 0.9930 0.0195
-12.500 -0.9260 0.02126 0.01724 -0.0952 0.9911 0.0201
-12.250 -0.8954 0.02078 0.01666 -0.0963 0.9894 0.0206
-12.000 -0.8682 0.01946 0.01525 -0.0976 0.9877 0.0214
-11.750 -0.8365 0.01894 0.01471 -0.0990 0.9866 0.0220
-11.500 -0.8038 0.01852 0.01424 -0.1004 0.9857 0.0227
-11.250 -0.7707 0.01808 0.01375 -0.1019 0.9849 0.0235
-11.000 -0.7369 0.01769 0.01328 -0.1035 0.9843 0.0242
-10.750 -0.7070 0.01745 0.01297 -0.1041 0.9819 0.0246
-10.500 -0.6803 0.01619 0.01161 -0.1049 0.9793 0.0257
-10.250 -0.6491 0.01569 0.01109 -0.1060 0.9775 0.0264
-10.000 -0.6172 0.01529 0.01065 -0.1071 0.9759 0.0271
-9.750 -0.5850 0.01491 0.01022 -0.1082 0.9742 0.0279
-9.500 -0.5547 0.01456 0.00981 -0.1089 0.9718 0.0287
-9.250 -0.5287 0.01426 0.00944 -0.1085 0.9665 0.0292
-9.000 -0.5023 0.01345 0.00855 -0.1085 0.9622 0.0299
-8.750 -0.4769 0.01285 0.00791 -0.1082 0.9574 0.0309
-8.500 -0.4513 0.01249 0.00752 -0.1078 0.9519 0.0317
-8.250 -0.4243 0.01214 0.00713 -0.1076 0.9474 0.0324
-8.000 -0.3979 0.01184 0.00678 -0.1073 0.9422 0.0333
-7.750 -0.3715 0.01155 0.00644 -0.1070 0.9363 0.0340
-7.500 -0.3442 0.01127 0.00609 -0.1068 0.9313 0.0345
-7.250 -0.3183 0.01080 0.00556 -0.1064 0.9249 0.0354
-7.000 -0.2921 0.01033 0.00505 -0.1061 0.9186 0.0365
-6.750 -0.2649 0.01003 0.00471 -0.1059 0.9125 0.0375
-6.500 -0.2377 0.00977 0.00441 -0.1057 0.9053 0.0384
-6.000 -0.1825 0.00935 0.00389 -0.1054 0.8910 0.0404
-5.750 -0.1549 0.00912 0.00360 -0.1052 0.8835 0.0414
-5.500 -0.1275 0.00880 0.00325 -0.1051 0.8751 0.0435
-5.000 -0.0718 0.00845 0.00283 -0.1049 0.8578 0.0476
-4.750 -0.0441 0.00824 0.00259 -0.1047 0.8488 0.0519
-4.500 -0.0162 0.00810 0.00243 -0.1046 0.8388 0.0569
-4.250 0.0117 0.00793 0.00228 -0.1045 0.8288 0.0655
-4.000 0.0394 0.00780 0.00213 -0.1044 0.8184 0.0745
-3.750 0.0674 0.00769 0.00201 -0.1044 0.8073 0.0820
-3.500 0.0954 0.00761 0.00191 -0.1043 0.7964 0.0890
-3.250 0.1232 0.00752 0.00180 -0.1042 0.7851 0.0977
-3.000 0.1512 0.00745 0.00171 -0.1041 0.7733 0.1066
-2.750 0.1791 0.00737 0.00163 -0.1040 0.7616 0.1182
-2.500 0.2069 0.00729 0.00156 -0.1040 0.7497 0.1332
-2.250 0.2346 0.00723 0.00150 -0.1039 0.7378 0.1502
-2.000 0.2625 0.00715 0.00145 -0.1038 0.7254 0.1697
-1.750 0.2903 0.00709 0.00142 -0.1038 0.7132 0.1927
-1.500 0.3180 0.00703 0.00141 -0.1037 0.7012 0.2214
-1.250 0.3456 0.00701 0.00139 -0.1036 0.6886 0.2466
-1.000 0.3734 0.00697 0.00138 -0.1035 0.6754 0.2686
-0.750 0.4012 0.00694 0.00137 -0.1035 0.6626 0.2903
-0.500 0.4288 0.00691 0.00138 -0.1034 0.6497 0.3203
-0.250 0.4562 0.00686 0.00139 -0.1033 0.6365 0.3629
0.000 0.4833 0.00678 0.00141 -0.1032 0.6232 0.4192
0.250 0.5102 0.00658 0.00146 -0.1031 0.6101 0.5177
0.500 0.5366 0.00635 0.00153 -0.1029 0.5975 0.6393
0.750 0.5622 0.00617 0.00160 -0.1024 0.5856 0.7449
1.000 0.5842 0.00594 0.00170 -0.1009 0.5740 0.8717
1.250 0.6163 0.00588 0.00177 -0.1014 0.5622 0.9842
1.500 0.6525 0.00598 0.00181 -0.1033 0.5505 1.0000
1.750 0.6788 0.00611 0.00186 -0.1029 0.5398 1.0000
2.000 0.7055 0.00622 0.00192 -0.1026 0.5294 1.0000
2.250 0.7325 0.00633 0.00199 -0.1024 0.5204 1.0000
2.500 0.7592 0.00646 0.00206 -0.1022 0.5112 1.0000
2.750 0.7865 0.00656 0.00213 -0.1020 0.5029 1.0000
3.250 0.8405 0.00681 0.00231 -0.1016 0.4847 1.0000
3.500 0.8672 0.00696 0.00240 -0.1014 0.4746 1.0000
3.750 0.8941 0.00709 0.00250 -0.1012 0.4646 1.0000
4.000 0.9210 0.00722 0.00260 -0.1010 0.4540 1.0000
4.250 0.9473 0.00739 0.00272 -0.1007 0.4426 1.0000
4.500 0.9734 0.00758 0.00284 -0.1004 0.4273 1.0000
4.750 0.9993 0.00778 0.00297 -0.1001 0.4110 1.0000
5.000 1.0254 0.00797 0.00311 -0.0998 0.3979 1.0000
5.250 1.0518 0.00813 0.00326 -0.0995 0.3861 1.0000
5.500 1.0777 0.00834 0.00342 -0.0992 0.3731 1.0000
5.750 1.1031 0.00857 0.00359 -0.0988 0.3575 1.0000
6.000 1.1280 0.00884 0.00379 -0.0983 0.3398 1.0000
6.250 1.1523 0.00914 0.00401 -0.0978 0.3207 1.0000
6.500 1.1761 0.00948 0.00426 -0.0971 0.2993 1.0000
6.750 1.1988 0.00989 0.00455 -0.0963 0.2737 1.0000
7.000 1.2208 0.01036 0.00488 -0.0954 0.2461 1.0000
7.250 1.2417 0.01089 0.00526 -0.0943 0.2173 1.0000
7.500 1.2614 0.01149 0.00569 -0.0931 0.1865 1.0000
7.750 1.2793 0.01220 0.00621 -0.0915 0.1526 1.0000
8.000 1.2973 0.01288 0.00672 -0.0900 0.1252 1.0000
8.250 1.3164 0.01345 0.00719 -0.0887 0.1065 1.0000
8.500 1.3346 0.01404 0.00769 -0.0872 0.0893 1.0000
8.750 1.3514 0.01469 0.00823 -0.0854 0.0729 1.0000
9.000 1.3676 0.01527 0.00875 -0.0836 0.0622 1.0000
9.250 1.3835 0.01581 0.00926 -0.0817 0.0563 1.0000
9.500 1.4004 0.01631 0.00976 -0.0799 0.0521 1.0000
9.750 1.4171 0.01682 0.01028 -0.0782 0.0491 1.0000
10.000 1.4317 0.01746 0.01091 -0.0762 0.0459 1.0000
10.250 1.4484 0.01797 0.01147 -0.0746 0.0442 1.0000
10.500 1.4653 0.01849 0.01203 -0.0731 0.0427 1.0000
10.750 1.4805 0.01911 0.01267 -0.0714 0.0411 1.0000
11.000 1.4938 0.01986 0.01343 -0.0695 0.0392 1.0000
11.250 1.5061 0.02069 0.01430 -0.0676 0.0376 1.0000
11.500 1.5221 0.02129 0.01495 -0.0662 0.0368 1.0000
11.750 1.5369 0.02199 0.01570 -0.0647 0.0356 1.0000
12.000 1.5500 0.02282 0.01656 -0.0631 0.0343 1.0000
12.250 1.5608 0.02382 0.01758 -0.0614 0.0330 1.0000
12.500 1.5688 0.02506 0.01888 -0.0594 0.0316 1.0000
12.750 1.5831 0.02588 0.01975 -0.0582 0.0308 1.0000
13.000 1.5959 0.02683 0.02075 -0.0569 0.0298 1.0000
13.250 1.6066 0.02796 0.02192 -0.0555 0.0286 1.0000
13.500 1.6141 0.02939 0.02338 -0.0540 0.0273 1.0000
13.750 1.6213 0.03089 0.02494 -0.0526 0.0262 1.0000
14.000 1.6325 0.03209 0.02620 -0.0516 0.0252 1.0000
14.250 1.6414 0.03354 0.02770 -0.0505 0.0241 1.0000
14.500 1.6474 0.03528 0.02947 -0.0493 0.0229 1.0000
14.750 1.6508 0.03731 0.03156 -0.0482 0.0218 1.0000
15.000 1.6585 0.03899 0.03332 -0.0474 0.0209 1.0000
15.250 1.6638 0.04096 0.03533 -0.0466 0.0198 1.0000
15.500 1.6661 0.04330 0.03772 -0.0458 0.0187 1.0000
15.750 1.6666 0.04589 0.04037 -0.0451 0.0179 1.0000
16.000 1.6698 0.04827 0.04284 -0.0447 0.0171 1.0000
16.250 1.6706 0.05099 0.04562 -0.0443 0.0164 1.0000
16.500 1.6692 0.05402 0.04871 -0.0440 0.0157 1.0000
16.750 1.6638 0.05759 0.05235 -0.0439 0.0151 1.0000
17.000 1.6605 0.06101 0.05587 -0.0439 0.0146 1.0000
17.250 1.6584 0.06435 0.05931 -0.0441 0.0142 1.0000
17.500 1.6548 0.06793 0.06298 -0.0444 0.0138 1.0000
17.750 1.6497 0.07175 0.06689 -0.0448 0.0134 1.0000
18.000 1.6430 0.07583 0.07106 -0.0453 0.0131 1.0000
18.250 1.6346 0.08024 0.07555 -0.0461 0.0128 1.0000
18.500 1.6237 0.08507 0.08047 -0.0470 0.0124 1.0000
18.750 1.6097 0.09040 0.08590 -0.0482 0.0121 1.0000
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