FX60-100 10.0% smoothed (fx60100sm-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX60-100 10.0% smoothed (fx60100sm-il) Reynolds number: 500,000 Max Cl/Cd: 91.48 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx60100sm-il-500000-n5.txt Download as CSV file: xf-fx60100sm-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX60-100 10.0% smoothed
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3855 0.08616 0.08387 -0.0394 1.0000 0.0093
-9.000 -0.3898 0.08227 0.08003 -0.0403 1.0000 0.0090
-8.500 -0.4474 0.04343 0.04095 -0.0779 0.9817 0.0071
-8.250 -0.4232 0.03334 0.03027 -0.0972 0.9720 0.0070
-8.000 -0.3985 0.02749 0.02384 -0.1044 0.9655 0.0070
-7.750 -0.3718 0.02359 0.01945 -0.1081 0.9595 0.0070
-7.500 -0.3416 0.02078 0.01621 -0.1108 0.9555 0.0071
-7.250 -0.3153 0.01871 0.01381 -0.1118 0.9490 0.0072
-7.000 -0.2872 0.01680 0.01165 -0.1130 0.9437 0.0074
-6.750 -0.2585 0.01577 0.01049 -0.1138 0.9387 0.0077
-6.500 -0.2312 0.01494 0.00953 -0.1140 0.9323 0.0079
-6.250 -0.2026 0.01418 0.00866 -0.1145 0.9269 0.0083
-6.000 -0.1752 0.01345 0.00782 -0.1146 0.9204 0.0087
-5.750 -0.1472 0.01276 0.00702 -0.1148 0.9140 0.0091
-5.500 -0.1192 0.01215 0.00631 -0.1150 0.9076 0.0095
-5.250 -0.0912 0.01164 0.00569 -0.1151 0.9005 0.0099
-5.000 -0.0629 0.01108 0.00505 -0.1154 0.8939 0.0107
-4.750 -0.0348 0.01067 0.00461 -0.1156 0.8865 0.0116
-4.500 -0.0063 0.01028 0.00415 -0.1157 0.8796 0.0124
-4.250 0.0222 0.00991 0.00370 -0.1159 0.8718 0.0133
-4.000 0.0508 0.00961 0.00331 -0.1160 0.8644 0.0143
-3.750 0.0794 0.00927 0.00290 -0.1161 0.8563 0.0164
-3.500 0.1079 0.00906 0.00263 -0.1162 0.8482 0.0189
-3.250 0.1365 0.00882 0.00234 -0.1162 0.8398 0.0249
-3.000 0.1653 0.00849 0.00207 -0.1165 0.8310 0.0531
-2.750 0.1944 0.00776 0.00178 -0.1172 0.8223 0.1866
-2.500 0.2230 0.00735 0.00164 -0.1176 0.8125 0.2818
-2.250 0.2514 0.00717 0.00158 -0.1178 0.8026 0.3389
-2.000 0.2796 0.00708 0.00155 -0.1178 0.7924 0.3838
-1.750 0.3078 0.00706 0.00150 -0.1177 0.7815 0.4020
-1.500 0.3360 0.00705 0.00146 -0.1176 0.7700 0.4149
-1.250 0.3641 0.00705 0.00143 -0.1175 0.7581 0.4285
-1.000 0.3921 0.00706 0.00141 -0.1174 0.7455 0.4410
-0.750 0.4201 0.00709 0.00139 -0.1173 0.7324 0.4525
-0.500 0.4479 0.00713 0.00138 -0.1171 0.7183 0.4638
-0.250 0.4757 0.00718 0.00139 -0.1170 0.7033 0.4744
0.000 0.5034 0.00723 0.00140 -0.1168 0.6873 0.4843
0.250 0.5309 0.00731 0.00142 -0.1166 0.6705 0.4944
0.500 0.5584 0.00739 0.00146 -0.1165 0.6533 0.5050
1.000 0.6131 0.00758 0.00157 -0.1161 0.6179 0.5259
1.250 0.6403 0.00770 0.00164 -0.1159 0.5978 0.5369
1.500 0.6672 0.00784 0.00173 -0.1156 0.5768 0.5483
1.750 0.6942 0.00798 0.00183 -0.1154 0.5550 0.5599
2.000 0.7208 0.00816 0.00194 -0.1151 0.5309 0.5719
2.250 0.7469 0.00839 0.00207 -0.1148 0.5001 0.5845
2.500 0.7729 0.00864 0.00222 -0.1144 0.4681 0.5975
2.750 0.7990 0.00887 0.00238 -0.1141 0.4397 0.6113
3.000 0.8250 0.00912 0.00255 -0.1138 0.4119 0.6260
3.250 0.8510 0.00937 0.00274 -0.1135 0.3847 0.6412
3.500 0.8771 0.00961 0.00295 -0.1132 0.3606 0.6580
3.750 0.9029 0.00987 0.00317 -0.1128 0.3343 0.6764
4.000 0.9281 0.01020 0.00342 -0.1124 0.3032 0.6965
4.250 0.9533 0.01051 0.00368 -0.1120 0.2747 0.7196
4.500 0.9782 0.01081 0.00397 -0.1116 0.2483 0.7478
5.000 1.0229 0.01133 0.00456 -0.1095 0.1938 0.8615
5.250 1.0447 0.01162 0.00483 -0.1083 0.1676 1.0000
5.750 1.0942 0.01250 0.00554 -0.1075 0.1292 1.0000
6.000 1.1189 0.01293 0.00590 -0.1071 0.1139 1.0000
6.250 1.1434 0.01336 0.00629 -0.1066 0.1017 1.0000
6.500 1.1678 0.01379 0.00669 -0.1061 0.0925 1.0000
6.750 1.1927 0.01415 0.00707 -0.1057 0.0860 1.0000
7.000 1.2166 0.01461 0.00750 -0.1051 0.0788 1.0000
7.250 1.2410 0.01498 0.00790 -0.1046 0.0738 1.0000
7.500 1.2645 0.01546 0.00837 -0.1040 0.0682 1.0000
7.750 1.2883 0.01586 0.00881 -0.1035 0.0635 1.0000
8.000 1.3113 0.01634 0.00928 -0.1028 0.0578 1.0000
8.250 1.3343 0.01680 0.00977 -0.1021 0.0533 1.0000
8.500 1.3570 0.01727 0.01025 -0.1014 0.0485 1.0000
8.750 1.3787 0.01782 0.01082 -0.1006 0.0435 1.0000
9.000 1.4004 0.01832 0.01134 -0.0998 0.0384 1.0000
9.250 1.4210 0.01892 0.01194 -0.0988 0.0333 1.0000
9.500 1.4409 0.01956 0.01258 -0.0978 0.0280 1.0000
9.750 1.4600 0.02024 0.01327 -0.0966 0.0231 1.0000
10.000 1.4776 0.02101 0.01405 -0.0953 0.0188 1.0000
10.250 1.4941 0.02184 0.01491 -0.0937 0.0151 1.0000
10.500 1.5100 0.02265 0.01578 -0.0921 0.0127 1.0000
10.750 1.5222 0.02358 0.01674 -0.0900 0.0106 1.0000
11.000 1.5343 0.02442 0.01767 -0.0878 0.0094 1.0000
11.250 1.5445 0.02539 0.01871 -0.0854 0.0084 1.0000
11.500 1.5527 0.02654 0.01994 -0.0830 0.0074 1.0000
11.750 1.5620 0.02763 0.02114 -0.0808 0.0069 1.0000
12.000 1.5705 0.02881 0.02243 -0.0787 0.0064 1.0000
12.250 1.5778 0.03014 0.02385 -0.0766 0.0059 1.0000
12.500 1.5836 0.03164 0.02547 -0.0746 0.0055 1.0000
12.750 1.5867 0.03346 0.02739 -0.0726 0.0051 1.0000
13.000 1.5906 0.03526 0.02932 -0.0708 0.0049 1.0000
13.250 1.5949 0.03710 0.03129 -0.0693 0.0047 1.0000
13.500 1.5975 0.03920 0.03352 -0.0680 0.0045 1.0000
13.750 1.5988 0.04153 0.03598 -0.0668 0.0044 1.0000
14.000 1.5986 0.04413 0.03873 -0.0659 0.0042 1.0000
14.250 1.5973 0.04701 0.04174 -0.0653 0.0041 1.0000
14.500 1.5944 0.05022 0.04509 -0.0650 0.0040 1.0000
14.750 1.5902 0.05377 0.04879 -0.0650 0.0039 1.0000
15.000 1.5844 0.05774 0.05290 -0.0655 0.0038 1.0000
15.250 1.5768 0.06218 0.05750 -0.0664 0.0038 1.0000
15.500 1.5678 0.06712 0.06259 -0.0678 0.0037 1.0000
15.750 1.5569 0.07263 0.06826 -0.0697 0.0036 1.0000
16.000 1.5439 0.07882 0.07462 -0.0722 0.0036 1.0000
16.250 1.5296 0.08560 0.08157 -0.0752 0.0036 1.0000
16.500 1.5130 0.09308 0.08922 -0.0788 0.0036 1.0000
16.750 1.4951 0.10117 0.09748 -0.0830 0.0036 1.0000
17.000 1.4761 0.10979 0.10627 -0.0876 0.0036 1.0000
17.250 1.4558 0.11894 0.11560 -0.0927 0.0036 1.0000
17.500 1.4350 0.12850 0.12532 -0.0981 0.0036 1.0000
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Polar data table (+)
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