WB-140/35/FB 14% (wb140-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: WB-140/35/FB 14% (wb140-il) Reynolds number: 100,000 Max Cl/Cd: 53.37 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-wb140-il-100000.txt Download as CSV file: xf-wb140-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: WB-140/35/FB 14%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.1941 0.10889 0.10449 -0.0742 0.9517 0.1354
-8.500 -0.2125 0.10801 0.10367 -0.0719 0.9455 0.1382
-8.250 -0.2235 0.10553 0.10124 -0.0735 0.9410 0.1400
-8.000 -0.2046 0.10202 0.09770 -0.0742 0.9390 0.1427
-7.750 -0.2146 0.10024 0.09597 -0.0740 0.9354 0.1461
-7.500 -0.2573 0.10088 0.09672 -0.0684 0.9291 0.1471
-7.250 -0.2563 0.09819 0.09406 -0.0674 0.9257 0.1486
-7.000 -0.2480 0.09524 0.09111 -0.0684 0.9228 0.1517
-6.750 -0.2771 0.09364 0.08959 -0.0684 0.9180 0.1550
-6.500 -0.2820 0.09195 0.08792 -0.0650 0.9141 0.1562
-6.250 -0.3325 0.06300 0.05821 -0.0919 0.9099 0.0857
-6.000 -0.3130 0.05058 0.04455 -0.0989 0.9082 0.0711
-5.750 -0.2799 0.04571 0.03915 -0.1026 0.9062 0.0694
-5.500 -0.2534 0.04300 0.03580 -0.1040 0.9035 0.0701
-5.250 -0.2365 0.04140 0.03375 -0.1031 0.9007 0.0706
-5.000 -0.2119 0.03979 0.03175 -0.1033 0.8976 0.0707
-4.750 -0.1814 0.03851 0.03013 -0.1041 0.8946 0.0711
-4.500 -0.1454 0.03709 0.02859 -0.1061 0.8918 0.0736
-4.250 -0.1026 0.03629 0.02773 -0.1091 0.8893 0.0783
-4.000 -0.0928 0.03613 0.02749 -0.1066 0.8850 0.0801
-3.750 -0.0709 0.03594 0.02720 -0.1060 0.8816 0.0828
-3.500 -0.0370 0.03553 0.02674 -0.1075 0.8775 0.0881
-3.250 0.0142 0.03501 0.02633 -0.1116 0.8735 0.1063
-3.000 0.0247 0.03510 0.02644 -0.1090 0.8652 0.1396
-2.750 0.0666 0.03533 0.02644 -0.1114 0.8596 0.2070
-2.500 0.0878 0.03589 0.02714 -0.1108 0.8532 0.2314
-2.250 0.1089 0.03653 0.02766 -0.1103 0.8475 0.2541
-2.000 0.1464 0.03683 0.02797 -0.1122 0.8434 0.2765
-1.750 0.1652 0.03734 0.02836 -0.1113 0.8370 0.2855
-1.500 0.1891 0.03767 0.02867 -0.1112 0.8308 0.2974
-1.250 0.2293 0.03772 0.02869 -0.1135 0.8269 0.3086
-1.000 0.2417 0.03840 0.02930 -0.1117 0.8194 0.3165
-0.750 0.2697 0.03871 0.02961 -0.1122 0.8137 0.3309
-0.500 0.3127 0.03865 0.02959 -0.1148 0.8100 0.3501
-0.250 0.3199 0.03933 0.03032 -0.1122 0.7998 0.3576
0.000 0.3638 0.03904 0.03000 -0.1145 0.7949 0.3673
0.250 0.3787 0.03952 0.03050 -0.1129 0.7846 0.3733
0.500 0.4208 0.03916 0.03013 -0.1149 0.7795 0.3827
0.750 0.4373 0.03968 0.03069 -0.1135 0.7698 0.3911
1.000 0.4778 0.03931 0.03038 -0.1153 0.7648 0.4093
1.250 0.4963 0.03976 0.03097 -0.1143 0.7553 0.4359
1.500 0.5313 0.03874 0.03092 -0.1151 0.7508 0.6671
1.750 0.5424 0.03879 0.03137 -0.1117 0.7411 1.0000
2.000 0.5816 0.03857 0.03098 -0.1131 0.7357 1.0000
2.250 0.6249 0.03813 0.03040 -0.1148 0.7318 1.0000
2.500 0.6414 0.03878 0.03098 -0.1134 0.7207 1.0000
2.750 0.6788 0.03854 0.03066 -0.1144 0.7159 1.0000
3.000 0.6997 0.03898 0.03106 -0.1134 0.7059 1.0000
3.250 0.7389 0.03845 0.03049 -0.1144 0.7015 1.0000
3.500 0.7581 0.03891 0.03092 -0.1132 0.6912 1.0000
3.750 0.8064 0.03767 0.02964 -0.1150 0.6894 1.0000
4.000 0.8143 0.03869 0.03068 -0.1125 0.6762 1.0000
4.250 0.8635 0.03712 0.02909 -0.1142 0.6746 1.0000
4.500 0.8711 0.03806 0.03004 -0.1117 0.6613 1.0000
4.750 0.9133 0.03677 0.02877 -0.1126 0.6582 1.0000
5.000 0.9273 0.03729 0.02932 -0.1107 0.6470 1.0000
5.250 0.9762 0.03549 0.02755 -0.1123 0.6455 1.0000
5.500 0.9858 0.03613 0.02824 -0.1098 0.6329 1.0000
5.750 1.0282 0.03460 0.02675 -0.1106 0.6289 1.0000
6.000 1.0505 0.03426 0.02646 -0.1093 0.6189 1.0000
6.250 1.1071 0.03165 0.02393 -0.1116 0.6168 1.0000
6.500 1.1232 0.03148 0.02381 -0.1094 0.6045 1.0000
6.750 1.1892 0.02845 0.02082 -0.1131 0.6006 1.0000
7.000 1.2095 0.02808 0.02051 -0.1113 0.5869 1.0000
7.250 1.2368 0.02747 0.01994 -0.1105 0.5731 1.0000
7.500 1.2672 0.02679 0.01928 -0.1101 0.5580 1.0000
7.750 1.2996 0.02614 0.01863 -0.1101 0.5410 1.0000
8.000 1.3345 0.02561 0.01802 -0.1106 0.5224 1.0000
8.250 1.3646 0.02557 0.01787 -0.1106 0.5024 1.0000
8.500 1.3828 0.02610 0.01834 -0.1090 0.4823 1.0000
8.750 1.4013 0.02667 0.01885 -0.1075 0.4628 1.0000
9.000 1.4190 0.02730 0.01938 -0.1059 0.4443 1.0000
9.250 1.4332 0.02802 0.02001 -0.1039 0.4264 1.0000
9.500 1.4435 0.02887 0.02082 -0.1014 0.4099 1.0000
9.750 1.4504 0.02983 0.02179 -0.0986 0.3947 1.0000
10.000 1.4574 0.03082 0.02283 -0.0959 0.3811 1.0000
10.250 1.4666 0.03176 0.02380 -0.0936 0.3689 1.0000
10.500 1.4769 0.03263 0.02464 -0.0915 0.3570 1.0000
10.750 1.4801 0.03383 0.02596 -0.0887 0.3454 1.0000
11.000 1.4840 0.03505 0.02723 -0.0861 0.3334 1.0000
11.250 1.4899 0.03623 0.02842 -0.0838 0.3218 1.0000
11.500 1.4965 0.03741 0.02959 -0.0816 0.3101 1.0000
11.750 1.4946 0.03912 0.03150 -0.0789 0.2990 1.0000
12.000 1.4938 0.04080 0.03325 -0.0764 0.2871 1.0000
12.250 1.4949 0.04244 0.03491 -0.0742 0.2755 1.0000
12.500 1.4901 0.04451 0.03695 -0.0717 0.2613 1.0000
12.750 1.4797 0.04717 0.03969 -0.0692 0.2460 1.0000
13.000 1.4692 0.05018 0.04290 -0.0672 0.2301 1.0000
13.250 1.4588 0.05346 0.04632 -0.0656 0.2112 1.0000
13.500 1.4452 0.05729 0.05014 -0.0640 0.1871 1.0000
13.750 1.4293 0.06167 0.05442 -0.0627 0.1537 1.0000
14.000 1.4072 0.06693 0.05939 -0.0614 0.0992 1.0000
14.250 1.3821 0.07283 0.06495 -0.0605 0.0775 1.0000
14.500 1.3627 0.07836 0.07043 -0.0600 0.0670 1.0000
14.750 1.3485 0.08351 0.07568 -0.0598 0.0610 1.0000
15.000 1.3331 0.08905 0.08132 -0.0601 0.0575 1.0000
15.250 1.3167 0.09495 0.08733 -0.0608 0.0553 1.0000
15.500 1.3057 0.10018 0.09275 -0.0616 0.0531 1.0000
15.750 1.2944 0.10558 0.09831 -0.0626 0.0512 1.0000
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Polar data table (+)
Polar graphs
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