HOBIESMO1.DAT (hobiesm-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: HOBIESMO1.DAT (hobiesm-il) Reynolds number: 200,000 Max Cl/Cd: 81.49 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hobiesm-il-200000.txt Download as CSV file: xf-hobiesm-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.3940 0.12370 0.11998 -0.0269 1.0000 0.0424
-10.750 -0.3955 0.12108 0.11740 -0.0299 1.0000 0.0428
-10.500 -0.3946 0.11796 0.11432 -0.0322 1.0000 0.0430
-10.250 -0.3910 0.11212 0.10851 -0.0319 1.0000 0.0439
-10.000 -0.3727 0.10926 0.10563 -0.0289 1.0000 0.0464
-9.750 -0.3668 0.10649 0.10287 -0.0293 1.0000 0.0489
-9.500 -0.3637 0.10348 0.09989 -0.0303 1.0000 0.0506
-9.250 -0.3656 0.10053 0.09700 -0.0326 1.0000 0.0532
-9.000 -0.2927 0.08538 0.08217 -0.0373 1.0000 0.0566
-8.750 -0.2850 0.08253 0.07933 -0.0361 1.0000 0.0581
-8.500 -0.2828 0.07961 0.07644 -0.0357 1.0000 0.0598
-8.250 -0.2846 0.07657 0.07346 -0.0356 1.0000 0.0620
-8.000 -0.2910 0.07368 0.07063 -0.0355 1.0000 0.0639
-7.750 -0.3100 0.07159 0.06865 -0.0348 1.0000 0.0656
-7.500 -0.3358 0.07099 0.06817 -0.0309 1.0000 0.0660
-7.250 -0.3611 0.07067 0.06795 -0.0263 1.0000 0.0660
-7.000 -0.3549 0.06222 0.05946 -0.0454 0.9929 0.0671
-6.750 -0.3420 0.05757 0.05485 -0.0406 0.9897 0.0689
-6.500 -0.3993 0.06435 0.06136 -0.0486 0.9958 0.0681
-6.250 -0.3689 0.04231 0.03877 -0.0678 0.9892 0.0417
-6.000 -0.3333 0.03179 0.02739 -0.0779 0.9844 0.0405
-5.750 -0.2994 0.02547 0.02015 -0.0824 0.9796 0.0398
-5.500 -0.2637 0.02201 0.01597 -0.0849 0.9748 0.0405
-5.250 -0.2242 0.02026 0.01372 -0.0875 0.9713 0.0427
-5.000 -0.1902 0.01794 0.01110 -0.0892 0.9667 0.0456
-4.750 -0.1548 0.01676 0.00981 -0.0908 0.9613 0.0490
-4.500 -0.1147 0.01579 0.00863 -0.0931 0.9578 0.0541
-4.250 -0.0793 0.01489 0.00772 -0.0947 0.9524 0.0643
-4.000 -0.0422 0.01404 0.00689 -0.0965 0.9471 0.0931
-3.750 -0.0001 0.01369 0.00657 -0.0994 0.9438 0.1310
-3.500 0.0355 0.01345 0.00626 -0.1010 0.9379 0.1513
-3.250 0.0719 0.01323 0.00605 -0.1027 0.9321 0.1721
-3.000 0.1115 0.01291 0.00569 -0.1050 0.9282 0.1930
-2.750 0.1410 0.01258 0.00538 -0.1052 0.9194 0.2088
-2.500 0.1772 0.01218 0.00503 -0.1067 0.9142 0.2306
-2.250 0.2052 0.01189 0.00481 -0.1066 0.9047 0.2544
-2.000 0.2369 0.01157 0.00456 -0.1071 0.8975 0.2870
-1.750 0.2649 0.01132 0.00441 -0.1069 0.8881 0.3247
-1.500 0.2923 0.01111 0.00430 -0.1066 0.8785 0.3652
-1.250 0.3211 0.01085 0.00415 -0.1064 0.8703 0.4090
-1.000 0.3463 0.01061 0.00407 -0.1057 0.8594 0.4605
-0.750 0.3709 0.01028 0.00403 -0.1048 0.8489 0.5390
-0.500 0.3914 0.00958 0.00400 -0.1027 0.8393 0.7392
-0.250 0.4362 0.00914 0.00378 -0.1055 0.8299 1.0000
0.000 0.4624 0.00920 0.00372 -0.1049 0.8183 1.0000
0.250 0.4888 0.00927 0.00368 -0.1043 0.8069 1.0000
0.500 0.5155 0.00933 0.00363 -0.1038 0.7956 1.0000
0.750 0.5423 0.00939 0.00360 -0.1033 0.7844 1.0000
1.000 0.5685 0.00947 0.00359 -0.1027 0.7720 1.0000
1.250 0.5946 0.00955 0.00361 -0.1021 0.7591 1.0000
1.500 0.6208 0.00963 0.00364 -0.1015 0.7461 1.0000
1.750 0.6470 0.00973 0.00369 -0.1010 0.7329 1.0000
2.000 0.6733 0.00983 0.00374 -0.1004 0.7195 1.0000
2.250 0.6994 0.00994 0.00381 -0.0999 0.7058 1.0000
2.500 0.7256 0.01006 0.00391 -0.0993 0.6918 1.0000
2.750 0.7516 0.01019 0.00401 -0.0988 0.6776 1.0000
3.000 0.7776 0.01033 0.00413 -0.0982 0.6631 1.0000
3.250 0.8035 0.01049 0.00427 -0.0976 0.6484 1.0000
3.500 0.8293 0.01067 0.00446 -0.0970 0.6336 1.0000
3.750 0.8550 0.01086 0.00464 -0.0965 0.6186 1.0000
4.000 0.8803 0.01105 0.00481 -0.0957 0.6016 1.0000
4.250 0.9036 0.01120 0.00491 -0.0946 0.5747 1.0000
4.500 0.9263 0.01140 0.00505 -0.0933 0.5443 1.0000
4.750 0.9485 0.01164 0.00523 -0.0920 0.5104 1.0000
5.000 0.9699 0.01196 0.00546 -0.0906 0.4704 1.0000
5.250 0.9858 0.01262 0.00574 -0.0883 0.3844 1.0000
5.500 0.9817 0.01555 0.00700 -0.0838 0.1164 1.0000
5.750 0.9925 0.01747 0.00848 -0.0812 0.0461 1.0000
6.000 1.0087 0.01872 0.00985 -0.0792 0.0383 1.0000
6.250 1.0268 0.01968 0.01096 -0.0775 0.0356 1.0000
6.500 1.0422 0.02085 0.01223 -0.0754 0.0334 1.0000
6.750 1.0564 0.02215 0.01357 -0.0733 0.0316 1.0000
7.000 1.0682 0.02390 0.01530 -0.0710 0.0293 1.0000
7.250 1.0845 0.02614 0.01754 -0.0692 0.0278 1.0000
7.500 1.1073 0.02773 0.01922 -0.0682 0.0272 1.0000
7.750 1.1330 0.02972 0.02131 -0.0676 0.0269 1.0000
8.000 1.1614 0.03238 0.02410 -0.0674 0.0272 1.0000
8.250 1.1949 0.03646 0.02828 -0.0680 0.0284 1.0000
8.500 1.2173 0.03854 0.03058 -0.0669 0.0287 1.0000
8.750 1.2374 0.04119 0.03349 -0.0656 0.0288 1.0000
14.000 0.8070 0.16197 0.15914 -0.0813 0.0582 1.0000
14.250 0.8054 0.16619 0.16337 -0.0836 0.0551 1.0000
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Polar data table (+)
Polar graphs
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