WORTMANN FX 66-17A-175 AIRFOIL (fx66a175-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: WORTMANN FX 66-17A-175 AIRFOIL (fx66a175-il) Reynolds number: 200,000 Max Cl/Cd: 70.12 at α=9.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx66a175-il-200000.txt Download as CSV file: xf-fx66a175-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 66-17A-175 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.1670 0.10544 0.10122 -0.0790 0.7306 0.0514
-11.250 -0.1613 0.10248 0.09817 -0.0801 0.7175 0.0540
-11.000 -0.1612 0.09861 0.09424 -0.0822 0.7080 0.0565
-10.750 -0.1184 0.08556 0.08131 -0.0804 0.6754 0.0623
-10.500 -0.1076 0.08327 0.07893 -0.0800 0.6692 0.0640
-10.250 -0.1042 0.07984 0.07550 -0.0809 0.6635 0.0664
-10.000 -0.1092 0.07507 0.07073 -0.0830 0.6599 0.0691
-7.750 -0.2924 0.03520 0.02855 -0.1059 0.6422 0.0334
-7.500 -0.2792 0.03149 0.02443 -0.1048 0.6376 0.0306
-7.250 -0.2616 0.02841 0.02082 -0.1035 0.6329 0.0289
-7.000 -0.2394 0.02647 0.01858 -0.1027 0.6287 0.0289
-6.750 -0.2164 0.02519 0.01715 -0.1022 0.6245 0.0302
-6.500 -0.1929 0.02414 0.01598 -0.1016 0.6198 0.0322
-6.250 -0.1688 0.02298 0.01465 -0.1009 0.6156 0.0335
-6.000 -0.1447 0.02193 0.01344 -0.1002 0.6123 0.0345
-5.750 -0.1213 0.02111 0.01257 -0.0994 0.6080 0.0358
-5.500 -0.1029 0.01967 0.01114 -0.0982 0.6042 0.0386
-5.250 -0.0799 0.01904 0.01046 -0.0977 0.6007 0.0440
-4.750 -0.0359 0.01726 0.00860 -0.0965 0.5938 0.0738
-4.500 -0.0254 0.01511 0.00813 -0.0953 0.5903 0.4184
-4.250 0.0023 0.01576 0.00860 -0.0948 0.5867 0.4668
-4.000 0.0298 0.01656 0.00927 -0.0941 0.5838 0.4949
-3.750 0.0562 0.01722 0.00992 -0.0933 0.5804 0.5152
-3.500 0.0827 0.01772 0.01041 -0.0926 0.5769 0.5306
-3.250 0.1094 0.01817 0.01084 -0.0918 0.5738 0.5446
-3.000 0.1365 0.01844 0.01103 -0.0913 0.5711 0.5544
-2.500 0.1902 0.01874 0.01119 -0.0908 0.5655 0.5699
-2.250 0.2175 0.01873 0.01106 -0.0911 0.5624 0.5755
-2.000 0.2446 0.01870 0.01095 -0.0910 0.5596 0.5797
-1.750 0.2723 0.01872 0.01088 -0.0911 0.5572 0.5835
-1.500 0.3008 0.01872 0.01074 -0.0915 0.5551 0.5866
-1.250 0.3281 0.01877 0.01068 -0.0918 0.5523 0.5903
-1.000 0.3545 0.01876 0.01067 -0.0918 0.5491 0.5933
-0.750 0.3815 0.01878 0.01066 -0.0918 0.5463 0.5962
-0.500 0.4094 0.01881 0.01062 -0.0921 0.5440 0.5988
-0.250 0.4377 0.01885 0.01055 -0.0925 0.5420 0.6012
0.000 0.4666 0.01897 0.01054 -0.0930 0.5402 0.6040
0.250 0.4925 0.01911 0.01069 -0.0930 0.5376 0.6066
0.500 0.5184 0.01920 0.01083 -0.0930 0.5347 0.6087
0.750 0.5453 0.01928 0.01091 -0.0931 0.5320 0.6108
1.000 0.5730 0.01936 0.01094 -0.0933 0.5297 0.6132
1.250 0.6014 0.01944 0.01096 -0.0937 0.5277 0.6157
1.500 0.6302 0.01961 0.01103 -0.0941 0.5260 0.6183
1.750 0.6552 0.01989 0.01137 -0.0941 0.5237 0.6209
2.000 0.6797 0.02014 0.01172 -0.0939 0.5212 0.6234
2.250 0.7053 0.02039 0.01202 -0.0938 0.5190 0.6262
2.500 0.7318 0.02060 0.01225 -0.0939 0.5169 0.6290
2.750 0.7592 0.02077 0.01242 -0.0942 0.5149 0.6319
3.000 0.7875 0.02096 0.01255 -0.0945 0.5132 0.6350
3.250 0.8156 0.02115 0.01275 -0.0949 0.5118 0.6377
3.500 0.8388 0.02159 0.01333 -0.0945 0.5097 0.6410
3.750 0.8602 0.02212 0.01399 -0.0940 0.5072 0.6447
4.000 0.8836 0.02259 0.01455 -0.0937 0.5050 0.6486
4.250 0.9080 0.02296 0.01500 -0.0936 0.5030 0.6521
4.500 0.9335 0.02327 0.01541 -0.0936 0.5013 0.6563
4.750 0.9596 0.02359 0.01578 -0.0936 0.4998 0.6611
5.000 0.9865 0.02390 0.01612 -0.0938 0.4985 0.6657
5.250 1.0138 0.02423 0.01653 -0.0941 0.4972 0.6704
5.500 1.0309 0.02510 0.01760 -0.0930 0.4949 0.6761
5.750 1.0439 0.02610 0.01883 -0.0915 0.4915 0.6819
6.000 1.0632 0.02680 0.01969 -0.0908 0.4891 0.6890
6.250 1.0855 0.02733 0.02035 -0.0904 0.4872 0.6967
6.500 1.1102 0.02772 0.02088 -0.0903 0.4858 0.7063
6.750 1.1357 0.02805 0.02133 -0.0903 0.4845 0.7180
7.000 1.1621 0.02839 0.02181 -0.0904 0.4833 0.7340
7.250 1.1601 0.03032 0.02410 -0.0872 0.4792 0.7559
7.500 1.1549 0.03207 0.02633 -0.0836 0.4746 0.8260
7.750 1.1883 0.03234 0.02681 -0.0853 0.4725 1.0000
8.000 1.2179 0.03254 0.02703 -0.0858 0.4710 1.0000
8.250 1.2501 0.03262 0.02715 -0.0866 0.4699 1.0000
8.500 1.2829 0.03227 0.02682 -0.0872 0.4671 1.0000
8.750 1.0941 0.04647 0.04127 -0.0687 0.4526 1.0000
9.000 1.1398 0.04510 0.03998 -0.0695 0.4528 1.0000
9.250 1.2243 0.03939 0.03435 -0.0722 0.4489 1.0000
9.500 1.3946 0.01989 0.01379 -0.0787 0.3597 1.0000
9.750 1.3670 0.02131 0.01478 -0.0708 0.2933 1.0000
10.000 1.3372 0.02393 0.01715 -0.0648 0.2505 1.0000
10.250 1.3073 0.02760 0.02068 -0.0609 0.2181 1.0000
10.500 1.2839 0.03168 0.02472 -0.0590 0.1969 1.0000
10.750 1.2536 0.03688 0.02984 -0.0575 0.1696 1.0000
11.000 1.2312 0.04153 0.03446 -0.0566 0.1504 1.0000
11.250 1.2044 0.04672 0.03955 -0.0557 0.1246 1.0000
11.500 1.1766 0.05210 0.04480 -0.0550 0.0963 1.0000
11.750 1.1498 0.05764 0.05015 -0.0546 0.0630 1.0000
12.000 1.1350 0.06214 0.05454 -0.0545 0.0417 1.0000
12.250 1.1187 0.06702 0.05931 -0.0544 0.0275 1.0000
12.500 1.1125 0.07087 0.06321 -0.0544 0.0232 1.0000
12.750 1.1109 0.07424 0.06671 -0.0545 0.0211 1.0000
13.000 1.1101 0.07759 0.07016 -0.0546 0.0200 1.0000
13.250 1.1079 0.08114 0.07382 -0.0549 0.0190 1.0000
13.500 1.1036 0.08505 0.07782 -0.0553 0.0182 1.0000
13.750 1.0993 0.08901 0.08188 -0.0557 0.0176 1.0000
14.000 1.0948 0.09297 0.08593 -0.0562 0.0171 1.0000
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Polar data table (+)
Polar graphs
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