FX 61-163 AIRFOIL (fx61163-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 61-163 AIRFOIL (fx61163-il) Reynolds number: 1,000,000 Max Cl/Cd: 115.71 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx61163-il-1000000-n5.txt Download as CSV file: xf-fx61163-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 61-163 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-14.500 -0.7146 0.07490 0.07275 -0.0548 1.0001 0.0034
-14.250 -0.7547 0.06370 0.06129 -0.0616 1.0001 0.0034
-14.000 -0.7750 0.05714 0.05456 -0.0650 1.0001 0.0034
-13.750 -0.7896 0.05216 0.04943 -0.0671 1.0001 0.0034
-13.500 -0.8006 0.04807 0.04520 -0.0683 1.0001 0.0034
-13.250 -0.8083 0.04466 0.04166 -0.0689 1.0001 0.0034
-13.000 -0.8142 0.04167 0.03854 -0.0690 1.0001 0.0034
-12.750 -0.8183 0.03904 0.03579 -0.0687 1.0001 0.0035
-12.500 -0.8152 0.03642 0.03303 -0.0695 0.9990 0.0035
-12.250 -0.8115 0.03406 0.03055 -0.0696 0.9886 0.0035
-12.000 -0.7533 0.03052 0.02672 -0.0821 0.9393 0.0036
-11.750 -0.7278 0.02878 0.02440 -0.0855 0.8253 0.0037
-11.500 -0.7187 0.02747 0.02281 -0.0848 0.7845 0.0038
-11.250 -0.7072 0.02620 0.02133 -0.0844 0.7564 0.0038
-11.000 -0.6938 0.02502 0.01996 -0.0839 0.7344 0.0039
-10.750 -0.6791 0.02387 0.01864 -0.0836 0.7170 0.0040
-10.500 -0.6630 0.02283 0.01745 -0.0833 0.7029 0.0041
-10.250 -0.6462 0.02185 0.01633 -0.0829 0.6909 0.0042
-10.000 -0.6298 0.02097 0.01533 -0.0824 0.6806 0.0043
-9.750 -0.6104 0.02013 0.01437 -0.0823 0.6719 0.0044
-9.500 -0.5894 0.01935 0.01348 -0.0824 0.6634 0.0045
-9.250 -0.5674 0.01858 0.01260 -0.0826 0.6563 0.0046
-9.000 -0.5446 0.01787 0.01179 -0.0829 0.6492 0.0047
-8.750 -0.5209 0.01723 0.01106 -0.0833 0.6436 0.0048
-8.500 -0.4967 0.01662 0.01037 -0.0836 0.6384 0.0048
-8.250 -0.4723 0.01606 0.00974 -0.0838 0.6334 0.0049
-8.000 -0.4474 0.01555 0.00916 -0.0841 0.6292 0.0050
-7.750 -0.4231 0.01480 0.00833 -0.0844 0.6250 0.0051
-7.500 -0.3982 0.01412 0.00758 -0.0848 0.6206 0.0052
-7.000 -0.3451 0.01315 0.00650 -0.0858 0.6131 0.0056
-6.750 -0.3175 0.01277 0.00609 -0.0863 0.6098 0.0058
-6.500 -0.2897 0.01243 0.00571 -0.0868 0.6065 0.0061
-6.250 -0.2617 0.01208 0.00531 -0.0874 0.6033 0.0063
-6.000 -0.2334 0.01176 0.00494 -0.0879 0.6002 0.0065
-5.750 -0.2045 0.01146 0.00460 -0.0886 0.5974 0.0068
-5.500 -0.1755 0.01119 0.00430 -0.0892 0.5943 0.0071
-5.250 -0.1464 0.01095 0.00402 -0.0898 0.5913 0.0074
-5.000 -0.1171 0.01069 0.00372 -0.0904 0.5883 0.0081
-4.750 -0.0879 0.01050 0.00350 -0.0910 0.5851 0.0091
-4.500 -0.0582 0.01031 0.00330 -0.0917 0.5824 0.0103
-4.250 -0.0283 0.01010 0.00309 -0.0924 0.5795 0.0147
-4.000 0.0018 0.00983 0.00289 -0.0933 0.5765 0.0322
-3.750 0.0323 0.00952 0.00268 -0.0943 0.5737 0.0634
-3.500 0.0647 0.00893 0.00238 -0.0961 0.5710 0.1545
-3.250 0.1036 0.00767 0.00188 -0.1002 0.5687 0.3675
-3.000 0.1400 0.00703 0.00166 -0.1029 0.5659 0.4945
-2.750 0.1725 0.00683 0.00161 -0.1042 0.5623 0.5478
-2.500 0.2033 0.00680 0.00162 -0.1050 0.5586 0.5772
-2.250 0.2333 0.00683 0.00163 -0.1055 0.5553 0.5892
-2.000 0.2635 0.00684 0.00161 -0.1060 0.5530 0.5948
-1.750 0.2935 0.00686 0.00160 -0.1065 0.5506 0.5985
-1.500 0.3235 0.00688 0.00161 -0.1070 0.5478 0.6029
-1.250 0.3533 0.00691 0.00161 -0.1075 0.5447 0.6079
-1.000 0.3830 0.00696 0.00161 -0.1079 0.5418 0.6123
-0.750 0.4128 0.00699 0.00164 -0.1084 0.5393 0.6159
-0.500 0.4426 0.00702 0.00166 -0.1089 0.5358 0.6196
-0.250 0.4723 0.00706 0.00168 -0.1094 0.5316 0.6230
0.000 0.5018 0.00711 0.00169 -0.1098 0.5276 0.6257
0.250 0.5314 0.00715 0.00171 -0.1102 0.5248 0.6279
0.500 0.5611 0.00718 0.00175 -0.1107 0.5219 0.6302
0.750 0.5907 0.00722 0.00180 -0.1112 0.5183 0.6325
1.000 0.6200 0.00727 0.00184 -0.1116 0.5143 0.6348
1.250 0.6493 0.00733 0.00188 -0.1120 0.5105 0.6370
1.500 0.6789 0.00738 0.00193 -0.1124 0.5069 0.6393
1.750 0.7082 0.00743 0.00197 -0.1128 0.5021 0.6414
2.000 0.7371 0.00751 0.00203 -0.1132 0.4964 0.6433
2.250 0.7664 0.00755 0.00210 -0.1136 0.4903 0.6452
2.500 0.7953 0.00763 0.00217 -0.1139 0.4843 0.6471
2.750 0.8242 0.00771 0.00225 -0.1143 0.4790 0.6490
3.000 0.8530 0.00780 0.00232 -0.1146 0.4708 0.6510
3.250 0.8815 0.00790 0.00242 -0.1149 0.4615 0.6530
3.500 0.9097 0.00803 0.00251 -0.1151 0.4516 0.6547
3.750 0.9375 0.00819 0.00262 -0.1153 0.4379 0.6562
4.000 0.9649 0.00838 0.00276 -0.1154 0.4215 0.6577
4.250 0.9920 0.00858 0.00292 -0.1154 0.4051 0.6594
4.500 1.0189 0.00881 0.00310 -0.1155 0.3879 0.6610
4.750 1.0458 0.00904 0.00329 -0.1155 0.3729 0.6626
5.000 1.0725 0.00927 0.00348 -0.1155 0.3588 0.6642
5.250 1.0992 0.00950 0.00368 -0.1155 0.3463 0.6657
5.500 1.1259 0.00973 0.00389 -0.1155 0.3353 0.6674
5.750 1.1523 0.00997 0.00410 -0.1155 0.3221 0.6691
6.000 1.1759 0.01044 0.00443 -0.1150 0.2929 0.6706
6.250 1.1974 0.01106 0.00485 -0.1143 0.2532 0.6721
6.500 1.2184 0.01170 0.00531 -0.1134 0.2185 0.6737
6.750 1.2391 0.01233 0.00580 -0.1125 0.1857 0.6753
7.000 1.2602 0.01291 0.00627 -0.1117 0.1615 0.6769
7.250 1.2775 0.01374 0.00689 -0.1103 0.1254 0.6784
7.500 1.2943 0.01457 0.00754 -0.1088 0.0939 0.6800
7.750 1.3110 0.01536 0.00818 -0.1073 0.0684 0.6817
8.000 1.3288 0.01602 0.00878 -0.1059 0.0531 0.6832
8.250 1.3480 0.01656 0.00929 -0.1048 0.0434 0.6845
8.500 1.3612 0.01742 0.01004 -0.1027 0.0268 0.6857
8.750 1.3760 0.01806 0.01067 -0.1009 0.0200 0.6870
9.000 1.3888 0.01866 0.01128 -0.0987 0.0160 0.6886
9.250 1.4029 0.01929 0.01194 -0.0968 0.0132 0.6902
9.500 1.4158 0.02000 0.01268 -0.0948 0.0100 0.6916
9.750 1.4245 0.02096 0.01365 -0.0925 0.0049 0.6931
10.000 1.4327 0.02201 0.01473 -0.0902 0.0028 0.6945
10.250 1.4435 0.02297 0.01575 -0.0885 0.0025 0.6959
10.500 1.4537 0.02407 0.01690 -0.0869 0.0022 0.6975
10.750 1.4632 0.02529 0.01818 -0.0855 0.0021 0.6991
11.000 1.4724 0.02665 0.01961 -0.0843 0.0019 0.7005
11.250 1.4805 0.02819 0.02123 -0.0832 0.0018 0.7019
11.500 1.4891 0.02979 0.02292 -0.0824 0.0017 0.7033
11.750 1.4973 0.03150 0.02471 -0.0816 0.0017 0.7048
12.000 1.5045 0.03334 0.02663 -0.0810 0.0017 0.7062
12.250 1.5110 0.03528 0.02866 -0.0804 0.0016 0.7077
12.500 1.5164 0.03739 0.03084 -0.0798 0.0016 0.7092
12.750 1.5208 0.03958 0.03311 -0.0793 0.0015 0.7108
13.000 1.5243 0.04188 0.03550 -0.0787 0.0015 0.7124
13.250 1.5268 0.04430 0.03799 -0.0782 0.0014 0.7140
13.500 1.5282 0.04685 0.04063 -0.0776 0.0014 0.7155
13.750 1.5289 0.04947 0.04333 -0.0772 0.0013 0.7168
14.000 1.5295 0.05214 0.04609 -0.0768 0.0013 0.7183
14.250 1.5291 0.05500 0.04904 -0.0764 0.0013 0.7198
14.500 1.5280 0.05798 0.05212 -0.0762 0.0012 0.7214
14.750 1.5270 0.06100 0.05523 -0.0760 0.0012 0.7230
15.000 1.5251 0.06421 0.05853 -0.0759 0.0012 0.7246
15.250 1.5226 0.06757 0.06198 -0.0760 0.0012 0.7262
15.500 1.5192 0.07107 0.06557 -0.0761 0.0012 0.7278
15.750 1.5152 0.07470 0.06929 -0.0763 0.0011 0.7293
16.000 1.5117 0.07835 0.07303 -0.0766 0.0011 0.7307
16.250 1.5065 0.08231 0.07710 -0.0771 0.0011 0.7324
16.500 1.5019 0.08623 0.08112 -0.0776 0.0011 0.7343
16.750 1.4954 0.09047 0.08547 -0.0783 0.0011 0.7362
17.000 1.4889 0.09478 0.08989 -0.0791 0.0011 0.7382
17.250 1.4805 0.09946 0.09467 -0.0802 0.0011 0.7402
17.500 1.4724 0.10415 0.09947 -0.0813 0.0010 0.7422
17.750 1.4635 0.10899 0.10442 -0.0826 0.0010 0.7440
18.000 1.4550 0.11385 0.10938 -0.0840 0.0010 0.7458
18.250 1.4457 0.11897 0.11461 -0.0857 0.0010 0.7477
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