FX60-100 10.0% smoothed (fx60100sm-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: FX60-100 10.0% smoothed (fx60100sm-il) Reynolds number: 200,000 Max Cl/Cd: 79.11 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx60100sm-il-200000-n5.txt Download as CSV file: xf-fx60100sm-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.2974 0.08509 0.08171 -0.0400 1.0000 0.0182
-9.250 -0.3744 0.09103 0.08742 -0.0395 1.0000 0.0185
-9.000 -0.3748 0.08786 0.08430 -0.0399 1.0000 0.0179
-8.750 -0.3778 0.08433 0.08080 -0.0405 1.0000 0.0172
-8.250 -0.4206 0.06939 0.06604 -0.0441 1.0000 0.0141
-8.000 -0.4405 0.06689 0.06364 -0.0418 1.0000 0.0140
-7.750 -0.4354 0.05735 0.05405 -0.0547 0.9928 0.0137
-7.500 -0.4109 0.04530 0.04154 -0.0776 0.9831 0.0134
-7.250 -0.3878 0.03876 0.03453 -0.0866 0.9755 0.0132
-7.000 -0.3566 0.03327 0.02846 -0.0936 0.9712 0.0131
-6.750 -0.3246 0.02912 0.02375 -0.0980 0.9673 0.0131
-6.500 -0.2939 0.02604 0.02016 -0.1007 0.9624 0.0133
-6.250 -0.2595 0.02353 0.01716 -0.1032 0.9592 0.0137
-6.000 -0.2237 0.02172 0.01495 -0.1055 0.9567 0.0141
-5.750 -0.1918 0.02004 0.01317 -0.1072 0.9532 0.0152
-5.500 -0.1620 0.01912 0.01214 -0.1081 0.9479 0.0165
-5.250 -0.1288 0.01791 0.01077 -0.1094 0.9441 0.0173
-5.000 -0.0942 0.01677 0.00951 -0.1109 0.9411 0.0179
-4.750 -0.0653 0.01589 0.00854 -0.1112 0.9348 0.0187
-4.500 -0.0329 0.01502 0.00760 -0.1123 0.9299 0.0196
-4.250 0.0017 0.01411 0.00661 -0.1140 0.9261 0.0215
-4.000 0.0302 0.01365 0.00609 -0.1143 0.9186 0.0250
-3.750 0.0630 0.01304 0.00536 -0.1153 0.9134 0.0289
-3.500 0.0934 0.01259 0.00482 -0.1158 0.9068 0.0359
-3.250 0.1249 0.01156 0.00420 -0.1171 0.9003 0.1341
-3.000 0.1556 0.01070 0.00398 -0.1183 0.8940 0.3049
-2.750 0.1845 0.01049 0.00396 -0.1185 0.8862 0.3827
-2.500 0.2136 0.01041 0.00391 -0.1185 0.8789 0.4262
-2.250 0.2424 0.01034 0.00379 -0.1184 0.8707 0.4431
-2.000 0.2709 0.01028 0.00368 -0.1183 0.8623 0.4583
-1.750 0.2999 0.01021 0.00357 -0.1182 0.8542 0.4730
-1.500 0.3277 0.01016 0.00349 -0.1180 0.8444 0.4862
-1.250 0.3561 0.01011 0.00341 -0.1179 0.8353 0.4989
-1.000 0.3844 0.01007 0.00332 -0.1177 0.8256 0.5108
-0.750 0.4122 0.01004 0.00327 -0.1174 0.8148 0.5228
-0.500 0.4401 0.01001 0.00322 -0.1172 0.8040 0.5344
-0.250 0.4680 0.00999 0.00318 -0.1170 0.7931 0.5459
0.000 0.4958 0.00998 0.00315 -0.1167 0.7813 0.5577
0.250 0.5234 0.00998 0.00315 -0.1164 0.7685 0.5698
0.500 0.5509 0.00999 0.00315 -0.1161 0.7550 0.5826
0.750 0.5783 0.01001 0.00316 -0.1158 0.7409 0.5957
1.000 0.6054 0.01004 0.00318 -0.1154 0.7259 0.6094
1.250 0.6324 0.01008 0.00322 -0.1150 0.7101 0.6235
1.500 0.6593 0.01014 0.00327 -0.1146 0.6937 0.6384
1.750 0.6860 0.01020 0.00335 -0.1141 0.6763 0.6542
2.000 0.7124 0.01028 0.00343 -0.1136 0.6579 0.6711
2.250 0.7385 0.01038 0.00352 -0.1131 0.6383 0.6896
2.500 0.7642 0.01049 0.00365 -0.1125 0.6174 0.7103
2.750 0.7893 0.01061 0.00376 -0.1117 0.5948 0.7335
3.000 0.8137 0.01075 0.00389 -0.1108 0.5687 0.7616
3.250 0.8367 0.01089 0.00402 -0.1096 0.5395 0.7989
3.500 0.8561 0.01093 0.00413 -0.1076 0.5113 0.8739
3.750 0.8813 0.01114 0.00427 -0.1070 0.4823 1.0000
4.000 0.9066 0.01149 0.00449 -0.1065 0.4537 1.0000
4.250 0.9315 0.01187 0.00475 -0.1060 0.4243 1.0000
4.500 0.9562 0.01227 0.00505 -0.1055 0.3945 1.0000
4.750 0.9806 0.01270 0.00536 -0.1050 0.3652 1.0000
5.000 1.0045 0.01318 0.00571 -0.1044 0.3333 1.0000
5.250 1.0277 0.01371 0.00609 -0.1038 0.2987 1.0000
5.500 1.0507 0.01428 0.00654 -0.1031 0.2645 1.0000
5.750 1.0735 0.01488 0.00701 -0.1025 0.2329 1.0000
6.000 1.0956 0.01555 0.00753 -0.1017 0.2012 1.0000
6.250 1.1175 0.01624 0.00809 -0.1010 0.1722 1.0000
6.500 1.1395 0.01692 0.00869 -0.1002 0.1490 1.0000
6.750 1.1613 0.01760 0.00930 -0.0994 0.1324 1.0000
7.000 1.1830 0.01827 0.00994 -0.0986 0.1188 1.0000
7.250 1.2047 0.01892 0.01060 -0.0978 0.1078 1.0000
7.500 1.2262 0.01957 0.01128 -0.0969 0.0994 1.0000
7.750 1.2463 0.02033 0.01206 -0.0959 0.0925 1.0000
8.000 1.2675 0.02096 0.01278 -0.0949 0.0864 1.0000
8.250 1.2867 0.02174 0.01358 -0.0938 0.0805 1.0000
8.500 1.3065 0.02245 0.01438 -0.0927 0.0757 1.0000
8.750 1.3257 0.02318 0.01517 -0.0916 0.0702 1.0000
9.000 1.3432 0.02402 0.01608 -0.0903 0.0652 1.0000
9.250 1.3621 0.02470 0.01687 -0.0891 0.0600 1.0000
9.500 1.3773 0.02564 0.01781 -0.0876 0.0550 1.0000
9.750 1.3950 0.02630 0.01863 -0.0862 0.0502 1.0000
10.000 1.4085 0.02717 0.01953 -0.0844 0.0453 1.0000
10.250 1.4223 0.02803 0.02052 -0.0826 0.0409 1.0000
10.500 1.4346 0.02899 0.02152 -0.0808 0.0358 1.0000
10.750 1.4457 0.03007 0.02272 -0.0789 0.0315 1.0000
11.000 1.4549 0.03132 0.02401 -0.0769 0.0271 1.0000
11.250 1.4633 0.03268 0.02549 -0.0750 0.0236 1.0000
11.500 1.4694 0.03427 0.02715 -0.0730 0.0207 1.0000
11.750 1.4736 0.03609 0.02908 -0.0710 0.0186 1.0000
12.000 1.4781 0.03795 0.03109 -0.0693 0.0167 1.0000
12.250 1.4800 0.04012 0.03336 -0.0677 0.0152 1.0000
12.500 1.4796 0.04261 0.03598 -0.0663 0.0140 1.0000
12.750 1.4806 0.04507 0.03862 -0.0651 0.0130 1.0000
13.000 1.4800 0.04783 0.04155 -0.0643 0.0122 1.0000
13.250 1.4774 0.05093 0.04482 -0.0637 0.0116 1.0000
13.500 1.4726 0.05445 0.04850 -0.0635 0.0112 1.0000
13.750 1.4652 0.05852 0.05273 -0.0638 0.0108 1.0000
14.000 1.4548 0.06322 0.05763 -0.0645 0.0105 1.0000
14.250 1.4454 0.06808 0.06266 -0.0657 0.0103 1.0000
14.500 1.4362 0.07316 0.06795 -0.0672 0.0101 1.0000
14.750 1.4258 0.07873 0.07372 -0.0693 0.0099 1.0000
15.000 1.4142 0.08480 0.07999 -0.0718 0.0098 1.0000
15.250 1.4014 0.09136 0.08675 -0.0748 0.0096 1.0000
15.500 1.3879 0.09836 0.09395 -0.0782 0.0095 1.0000
15.750 1.3735 0.10582 0.10159 -0.0821 0.0094 1.0000
16.000 1.3585 0.11369 0.10965 -0.0864 0.0094 1.0000
16.250 1.3435 0.12185 0.11799 -0.0911 0.0094 1.0000
16.500 1.3278 0.13041 0.12672 -0.0961 0.0093 1.0000
16.750 1.3124 0.13921 0.13568 -0.1014 0.0093 1.0000
17.000 1.2971 0.14825 0.14487 -0.1070 0.0094 1.0000
17.250 1.2820 0.15756 0.15434 -0.1129 0.0094 1.0000
17.500 1.2669 0.16721 0.16412 -0.1190 0.0094 1.0000
17.750 1.2514 0.17735 0.17439 -0.1255 0.0095 1.0000
18.000 1.2348 0.18831 0.18544 -0.1326 0.0096 1.0000
18.250 1.2143 0.20141 0.19864 -0.1408 0.0097 1.0000
|
Polar data table (+)
Polar graphs
<< Back to FX60-100 10.0% smoothed (fx60100sm-il)