HOBIESMO1.DAT (hobiesm-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: HOBIESMO1.DAT (hobiesm-il) Reynolds number: 100,000 Max Cl/Cd: 60.89 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hobiesm-il-100000.txt Download as CSV file: xf-hobiesm-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: HOBIESMO1.DAT
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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3593 0.09788 0.09306 -0.0324 1.0000 0.1054
-8.250 -0.3820 0.09749 0.09286 -0.0349 1.0000 0.1068
-8.000 -0.3985 0.09605 0.09158 -0.0390 1.0000 0.1072
-7.750 -0.3623 0.08905 0.08446 -0.0319 1.0000 0.1105
-7.500 -0.3609 0.08661 0.08208 -0.0305 1.0000 0.1133
-7.250 -0.3682 0.08463 0.08021 -0.0294 1.0000 0.1161
-7.000 -0.3847 0.08302 0.07874 -0.0323 1.0000 0.1198
-6.750 -0.4019 0.08043 0.07624 -0.0393 1.0000 0.1214
-6.500 -0.3986 0.07730 0.07318 -0.0328 1.0000 0.1226
-6.250 -0.3977 0.07501 0.07093 -0.0290 1.0000 0.1246
-6.000 -0.3985 0.07283 0.06878 -0.0275 1.0000 0.1276
-5.750 -0.3964 0.06811 0.06394 -0.0395 1.0000 0.1357
-5.500 -0.3709 0.04853 0.04357 -0.0561 1.0000 0.0798
-5.250 -0.3596 0.04525 0.04033 -0.0559 1.0000 0.0817
-5.000 -0.3378 0.03945 0.03413 -0.0588 1.0000 0.0767
-4.750 -0.3093 0.03260 0.02649 -0.0628 1.0000 0.0729
-4.500 -0.2804 0.02825 0.02135 -0.0648 1.0000 0.0731
-4.250 -0.2544 0.02598 0.01847 -0.0652 1.0000 0.0774
-4.000 -0.2300 0.02417 0.01626 -0.0653 1.0000 0.0828
-3.750 -0.2002 0.02284 0.01463 -0.0660 0.9982 0.0898
-3.500 -0.1573 0.02159 0.01302 -0.0690 0.9924 0.1074
-3.250 -0.1161 0.02076 0.01231 -0.0721 0.9856 0.1437
-3.000 -0.0762 0.02068 0.01221 -0.0750 0.9777 0.1840
-2.750 -0.0331 0.02063 0.01212 -0.0784 0.9705 0.2167
-2.500 0.0038 0.02030 0.01176 -0.0805 0.9615 0.2393
-2.250 0.0467 0.01999 0.01134 -0.0836 0.9544 0.2644
-2.000 0.0842 0.01961 0.01102 -0.0857 0.9454 0.2885
-1.750 0.1224 0.01929 0.01074 -0.0878 0.9367 0.3222
-1.500 0.1655 0.01882 0.01045 -0.0908 0.9295 0.3673
-1.250 0.1995 0.01844 0.01025 -0.0921 0.9196 0.4216
-1.000 0.2462 0.01778 0.00995 -0.0955 0.9141 0.5072
-0.750 0.2767 0.01702 0.00987 -0.0956 0.9041 0.6567
-0.500 0.3387 0.01612 0.00930 -0.1015 0.9002 1.0000
-0.250 0.3733 0.01619 0.00918 -0.1027 0.8891 1.0000
0.000 0.4103 0.01620 0.00904 -0.1042 0.8792 1.0000
0.250 0.4527 0.01606 0.00877 -0.1064 0.8717 1.0000
0.500 0.4832 0.01612 0.00875 -0.1066 0.8597 1.0000
0.750 0.5143 0.01616 0.00873 -0.1068 0.8482 1.0000
1.000 0.5463 0.01616 0.00867 -0.1071 0.8374 1.0000
1.250 0.5809 0.01603 0.00849 -0.1076 0.8281 1.0000
1.500 0.6079 0.01612 0.00855 -0.1070 0.8152 1.0000
1.750 0.6349 0.01621 0.00863 -0.1064 0.8023 1.0000
2.000 0.6619 0.01629 0.00870 -0.1057 0.7894 1.0000
2.250 0.6888 0.01637 0.00878 -0.1050 0.7766 1.0000
2.500 0.7158 0.01645 0.00886 -0.1043 0.7637 1.0000
2.750 0.7426 0.01652 0.00897 -0.1035 0.7506 1.0000
3.000 0.7694 0.01660 0.00907 -0.1028 0.7374 1.0000
3.250 0.7960 0.01669 0.00918 -0.1020 0.7239 1.0000
3.500 0.8224 0.01679 0.00932 -0.1011 0.7100 1.0000
3.750 0.8485 0.01690 0.00951 -0.1003 0.6956 1.0000
4.000 0.8745 0.01704 0.00971 -0.0994 0.6809 1.0000
4.250 0.9003 0.01720 0.00995 -0.0986 0.6658 1.0000
4.500 0.9261 0.01737 0.01020 -0.0977 0.6503 1.0000
4.750 0.9523 0.01722 0.01008 -0.0963 0.6299 1.0000
5.000 0.9732 0.01683 0.00965 -0.0936 0.5942 1.0000
5.250 0.9945 0.01663 0.00937 -0.0912 0.5583 1.0000
5.500 1.0120 0.01662 0.00933 -0.0885 0.5105 1.0000
5.750 1.0252 0.01689 0.00940 -0.0849 0.4322 1.0000
6.000 1.0223 0.01899 0.01006 -0.0798 0.2117 1.0000
6.250 1.0222 0.02210 0.01199 -0.0761 0.0766 1.0000
6.500 1.0359 0.02364 0.01357 -0.0737 0.0655 1.0000
6.750 1.0475 0.02521 0.01524 -0.0712 0.0593 1.0000
7.000 1.0594 0.02666 0.01678 -0.0688 0.0543 1.0000
7.250 1.0690 0.02846 0.01858 -0.0661 0.0517 1.0000
7.500 1.0864 0.03083 0.02083 -0.0644 0.0500 1.0000
7.750 1.1147 0.03282 0.02290 -0.0638 0.0490 1.0000
8.000 1.1431 0.03485 0.02509 -0.0634 0.0473 1.0000
8.250 1.1703 0.03711 0.02753 -0.0628 0.0452 1.0000
8.500 1.1992 0.04008 0.03077 -0.0623 0.0457 1.0000
8.750 1.2238 0.04349 0.03451 -0.0614 0.0471 1.0000
9.000 1.2459 0.04788 0.03921 -0.0605 0.0490 1.0000
9.250 1.2670 0.05030 0.04208 -0.0585 0.0526 1.0000
9.500 1.2723 0.05514 0.04774 -0.0551 0.0593 1.0000
9.750 1.2792 0.06068 0.05402 -0.0519 0.0715 1.0000
10.000 1.2589 0.07418 0.06898 -0.0476 0.1239 1.0000
10.250 1.2212 0.07679 0.07197 -0.0436 0.1221 1.0000
10.500 1.1888 0.08021 0.07558 -0.0408 0.1210 1.0000
10.750 1.1574 0.08510 0.08060 -0.0404 0.1213 1.0000
11.000 1.1287 0.09112 0.08673 -0.0418 0.1223 1.0000
11.250 1.0991 0.09829 0.09396 -0.0450 0.1231 1.0000
11.500 1.0684 0.10684 0.10256 -0.0500 0.1236 1.0000
11.750 1.0327 0.11799 0.11369 -0.0580 0.1237 1.0000
12.000 0.9875 0.13177 0.12735 -0.0697 0.1206 1.0000
12.250 0.9278 0.11123 0.10721 -0.0464 0.0770 1.0000
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Polar data table (+)
Polar graphs
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