HOBIESMO1.DAT (hobiesm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: HOBIESMO1.DAT (hobiesm-il) Reynolds number: 1,000,000 Max Cl/Cd: 130.71 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hobiesm-il-1000000.txt Download as CSV file: xf-hobiesm-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3226 0.07908 0.07759 -0.0368 1.0000 0.0109
-9.500 -0.3313 0.07340 0.07193 -0.0381 1.0000 0.0107
-9.250 -0.5919 0.02740 0.02502 -0.0847 0.9949 0.0078
-9.000 -0.5603 0.02546 0.02284 -0.0879 0.9920 0.0080
-8.750 -0.5354 0.01897 0.01562 -0.0935 0.9868 0.0087
-8.500 -0.5019 0.01787 0.01440 -0.0956 0.9845 0.0091
-8.250 -0.4688 0.01713 0.01356 -0.0974 0.9817 0.0096
-8.000 -0.4385 0.01613 0.01241 -0.0985 0.9763 0.0101
-7.750 -0.4050 0.01515 0.01127 -0.1002 0.9723 0.0107
-7.500 -0.3722 0.01453 0.01052 -0.1016 0.9668 0.0113
-7.250 -0.3407 0.01351 0.00930 -0.1028 0.9591 0.0119
-7.000 -0.3113 0.01208 0.00771 -0.1038 0.9495 0.0131
-6.750 -0.2808 0.01163 0.00719 -0.1045 0.9393 0.0140
-6.500 -0.2526 0.01111 0.00654 -0.1047 0.9274 0.0149
-6.250 -0.2256 0.01069 0.00600 -0.1045 0.9151 0.0157
-6.000 -0.1988 0.01036 0.00556 -0.1042 0.9035 0.0163
-5.750 -0.1728 0.00979 0.00484 -0.1039 0.8929 0.0172
-5.500 -0.1470 0.00909 0.00398 -0.1035 0.8829 0.0187
-5.250 -0.1204 0.00873 0.00353 -0.1032 0.8733 0.0199
-5.000 -0.0934 0.00845 0.00316 -0.1029 0.8642 0.0212
-4.750 -0.0664 0.00824 0.00285 -0.1027 0.8557 0.0225
-4.500 -0.0392 0.00806 0.00260 -0.1024 0.8468 0.0234
-4.250 -0.0121 0.00772 0.00216 -0.1022 0.8387 0.0271
-4.000 0.0151 0.00747 0.00189 -0.1019 0.8303 0.0352
-3.750 0.0418 0.00708 0.00166 -0.1017 0.8221 0.0769
-3.250 0.0966 0.00687 0.00145 -0.1014 0.8056 0.1034
-3.000 0.1241 0.00681 0.00135 -0.1012 0.7975 0.1120
-2.750 0.1517 0.00674 0.00126 -0.1011 0.7888 0.1210
-2.500 0.1791 0.00665 0.00118 -0.1010 0.7803 0.1332
-2.250 0.2065 0.00658 0.00110 -0.1008 0.7715 0.1472
-2.000 0.2340 0.00647 0.00104 -0.1007 0.7623 0.1686
-1.750 0.2613 0.00638 0.00098 -0.1005 0.7531 0.1925
-1.500 0.2886 0.00631 0.00094 -0.1003 0.7433 0.2176
-1.250 0.3160 0.00623 0.00091 -0.1002 0.7330 0.2416
-1.000 0.3434 0.00619 0.00088 -0.1000 0.7225 0.2656
-0.750 0.3707 0.00615 0.00087 -0.0998 0.7116 0.2901
-0.500 0.3978 0.00612 0.00086 -0.0996 0.6996 0.3167
-0.250 0.4251 0.00609 0.00087 -0.0995 0.6872 0.3440
0.000 0.4522 0.00607 0.00088 -0.0993 0.6743 0.3712
0.250 0.4793 0.00605 0.00089 -0.0991 0.6610 0.4026
0.500 0.5062 0.00601 0.00092 -0.0989 0.6471 0.4419
0.750 0.5326 0.00593 0.00097 -0.0986 0.6329 0.5076
1.000 0.5580 0.00571 0.00105 -0.0982 0.6187 0.6374
1.250 0.5914 0.00502 0.00113 -0.0993 0.6038 1.0000
1.500 0.6181 0.00513 0.00118 -0.0990 0.5893 1.0000
1.750 0.6449 0.00525 0.00124 -0.0987 0.5751 1.0000
2.000 0.6716 0.00537 0.00130 -0.0984 0.5608 1.0000
2.250 0.6983 0.00550 0.00137 -0.0982 0.5469 1.0000
2.500 0.7250 0.00563 0.00146 -0.0979 0.5332 1.0000
2.750 0.7517 0.00576 0.00155 -0.0976 0.5194 1.0000
3.000 0.7777 0.00595 0.00165 -0.0972 0.4974 1.0000
3.250 0.8033 0.00617 0.00177 -0.0968 0.4726 1.0000
3.500 0.8292 0.00637 0.00190 -0.0964 0.4489 1.0000
3.750 0.8542 0.00667 0.00205 -0.0959 0.4164 1.0000
4.000 0.8792 0.00695 0.00222 -0.0954 0.3850 1.0000
4.250 0.9019 0.00748 0.00247 -0.0946 0.3266 1.0000
4.500 0.9217 0.00832 0.00289 -0.0933 0.2396 1.0000
4.750 0.9306 0.01039 0.00396 -0.0906 0.0448 1.0000
5.000 0.9532 0.01101 0.00446 -0.0896 0.0206 1.0000
5.250 0.9780 0.01133 0.00482 -0.0891 0.0175 1.0000
5.500 1.0016 0.01179 0.00528 -0.0883 0.0144 1.0000
5.750 1.0250 0.01228 0.00584 -0.0875 0.0129 1.0000
6.000 1.0489 0.01267 0.00627 -0.0868 0.0119 1.0000
6.250 1.0722 0.01311 0.00674 -0.0860 0.0110 1.0000
6.500 1.0946 0.01363 0.00729 -0.0851 0.0101 1.0000
6.750 1.1090 0.01497 0.00877 -0.0828 0.0091 1.0000
7.000 1.1330 0.01527 0.00910 -0.0822 0.0087 1.0000
7.250 1.1545 0.01580 0.00968 -0.0812 0.0082 1.0000
7.500 1.1737 0.01653 0.01047 -0.0798 0.0078 1.0000
7.750 1.1926 0.01726 0.01125 -0.0784 0.0075 1.0000
8.000 1.2107 0.01803 0.01208 -0.0769 0.0072 1.0000
8.250 1.2284 0.01881 0.01290 -0.0754 0.0069 1.0000
8.500 1.2449 0.01966 0.01381 -0.0737 0.0067 1.0000
8.750 1.2585 0.02078 0.01500 -0.0716 0.0065 1.0000
9.000 1.2643 0.02336 0.01770 -0.0685 0.0061 1.0000
9.250 1.2795 0.02477 0.01924 -0.0667 0.0059 1.0000
9.500 1.2943 0.02593 0.02051 -0.0649 0.0058 1.0000
9.750 1.3081 0.02740 0.02212 -0.0629 0.0056 1.0000
10.000 1.3218 0.02962 0.02452 -0.0611 0.0055 1.0000
10.250 1.3338 0.03238 0.02751 -0.0592 0.0055 1.0000
10.500 1.3412 0.03492 0.03027 -0.0566 0.0054 1.0000
10.750 1.3436 0.03761 0.03319 -0.0535 0.0053 1.0000
11.000 1.3406 0.04071 0.03656 -0.0502 0.0053 1.0000
11.250 1.3311 0.04423 0.04034 -0.0466 0.0054 1.0000
11.500 1.3192 0.04760 0.04393 -0.0434 0.0055 1.0000
11.750 1.2982 0.05208 0.04864 -0.0406 0.0057 1.0000
12.000 1.2534 0.06318 0.06036 -0.0372 0.0074 1.0000
12.250 1.2363 0.06734 0.06467 -0.0369 0.0073 1.0000
12.500 1.2166 0.07230 0.06979 -0.0375 0.0073 1.0000
12.750 1.1978 0.07755 0.07519 -0.0389 0.0073 1.0000
13.000 1.1759 0.08392 0.08171 -0.0415 0.0073 1.0000
13.250 1.1525 0.09126 0.08919 -0.0452 0.0074 1.0000
13.500 1.1338 0.09828 0.09634 -0.0493 0.0073 1.0000
13.750 1.1055 0.10844 0.10665 -0.0557 0.0076 1.0000
14.000 1.0809 0.11888 0.11721 -0.0627 0.0078 1.0000
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Polar data table (+)
Polar graphs
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