HOBIESMO1.DAT (hobiesm-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: HOBIESMO1.DAT (hobiesm-il) Reynolds number: 500,000 Max Cl/Cd: 101.89 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hobiesm-il-500000-n5.txt Download as CSV file: xf-hobiesm-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4194 0.09630 0.09402 -0.0310 1.0000 0.0071
-10.000 -0.4308 0.08954 0.08731 -0.0336 1.0000 0.0075
-9.500 -0.6170 0.02867 0.02575 -0.0841 0.9919 0.0065
-9.250 -0.5891 0.02533 0.02203 -0.0883 0.9865 0.0069
-9.000 -0.5595 0.02261 0.01894 -0.0915 0.9821 0.0073
-8.750 -0.5324 0.02062 0.01663 -0.0931 0.9754 0.0078
-8.500 -0.5011 0.01902 0.01473 -0.0951 0.9710 0.0083
-8.250 -0.4719 0.01738 0.01284 -0.0966 0.9649 0.0089
-8.000 -0.4400 0.01673 0.01210 -0.0980 0.9590 0.0096
-7.750 -0.4075 0.01620 0.01148 -0.0994 0.9528 0.0105
-7.500 -0.3753 0.01552 0.01063 -0.1007 0.9451 0.0116
-7.250 -0.3436 0.01476 0.00968 -0.1019 0.9365 0.0125
-7.000 -0.3120 0.01422 0.00898 -0.1028 0.9272 0.0131
-6.750 -0.2842 0.01303 0.00758 -0.1033 0.9157 0.0144
-6.500 -0.2564 0.01251 0.00696 -0.1035 0.9045 0.0157
-6.250 -0.2289 0.01207 0.00640 -0.1035 0.8938 0.0169
-6.000 -0.2019 0.01163 0.00580 -0.1034 0.8837 0.0179
-5.750 -0.1750 0.01127 0.00531 -0.1032 0.8736 0.0190
-5.500 -0.1481 0.01098 0.00490 -0.1030 0.8640 0.0197
-5.250 -0.1213 0.01058 0.00437 -0.1027 0.8550 0.0204
-5.000 -0.0945 0.01017 0.00382 -0.1025 0.8459 0.0216
-4.750 -0.0675 0.00986 0.00339 -0.1022 0.8373 0.0231
-4.500 -0.0405 0.00961 0.00307 -0.1020 0.8290 0.0254
-4.250 -0.0133 0.00939 0.00277 -0.1018 0.8202 0.0282
-4.000 0.0138 0.00913 0.00248 -0.1016 0.8119 0.0375
-3.750 0.0407 0.00883 0.00225 -0.1014 0.8032 0.0626
-3.500 0.0679 0.00867 0.00208 -0.1012 0.7947 0.0796
-3.250 0.0952 0.00857 0.00194 -0.1010 0.7862 0.0908
-3.000 0.1225 0.00846 0.00182 -0.1009 0.7771 0.1016
-2.750 0.1498 0.00836 0.00171 -0.1007 0.7683 0.1127
-2.250 0.2043 0.00817 0.00151 -0.1003 0.7494 0.1400
-2.000 0.2315 0.00808 0.00143 -0.1002 0.7398 0.1579
-1.750 0.2587 0.00801 0.00135 -0.1000 0.7298 0.1752
-1.500 0.2859 0.00794 0.00129 -0.0998 0.7189 0.1922
-1.250 0.3131 0.00788 0.00125 -0.0996 0.7079 0.2139
-1.000 0.3402 0.00783 0.00121 -0.0994 0.6965 0.2349
-0.750 0.3672 0.00781 0.00119 -0.0992 0.6848 0.2559
-0.500 0.3942 0.00779 0.00118 -0.0989 0.6723 0.2769
-0.250 0.4212 0.00778 0.00118 -0.0987 0.6597 0.2997
0.000 0.4480 0.00777 0.00119 -0.0985 0.6465 0.3258
0.250 0.4748 0.00777 0.00121 -0.0982 0.6330 0.3518
1.250 0.5803 0.00763 0.00144 -0.0971 0.5780 0.5426
1.500 0.6031 0.00725 0.00157 -0.0961 0.5648 0.7278
1.750 0.6381 0.00686 0.00163 -0.0974 0.5507 1.0000
2.000 0.6647 0.00700 0.00170 -0.0971 0.5375 1.0000
2.250 0.6912 0.00714 0.00179 -0.0968 0.5243 1.0000
2.500 0.7176 0.00729 0.00191 -0.0965 0.5112 1.0000
2.750 0.7440 0.00744 0.00202 -0.0961 0.4982 1.0000
3.000 0.7703 0.00760 0.00215 -0.0958 0.4852 1.0000
3.250 0.7959 0.00782 0.00230 -0.0954 0.4655 1.0000
3.500 0.8212 0.00806 0.00246 -0.0949 0.4408 1.0000
3.750 0.8462 0.00833 0.00263 -0.0944 0.4139 1.0000
4.000 0.8708 0.00864 0.00284 -0.0938 0.3845 1.0000
4.250 0.8930 0.00918 0.00311 -0.0929 0.3299 1.0000
4.500 0.9136 0.00992 0.00352 -0.0918 0.2599 1.0000
4.750 0.9325 0.01087 0.00404 -0.0906 0.1781 1.0000
5.000 0.9441 0.01266 0.00507 -0.0883 0.0345 1.0000
5.250 0.9676 0.01312 0.00550 -0.0876 0.0224 1.0000
5.500 0.9912 0.01354 0.00592 -0.0869 0.0177 1.0000
5.750 1.0146 0.01400 0.00643 -0.0861 0.0147 1.0000
6.000 1.0380 0.01442 0.00692 -0.0854 0.0127 1.0000
6.250 1.0604 0.01493 0.00745 -0.0846 0.0107 1.0000
6.500 1.0815 0.01558 0.00817 -0.0834 0.0095 1.0000
6.750 1.1031 0.01614 0.00880 -0.0824 0.0089 1.0000
7.000 1.1238 0.01677 0.00950 -0.0813 0.0083 1.0000
7.250 1.1436 0.01744 0.01024 -0.0801 0.0077 1.0000
7.500 1.1627 0.01815 0.01104 -0.0787 0.0072 1.0000
7.750 1.1813 0.01886 0.01179 -0.0774 0.0066 1.0000
8.000 1.1932 0.02012 0.01315 -0.0750 0.0060 1.0000
8.250 1.2100 0.02090 0.01400 -0.0734 0.0057 1.0000
8.500 1.2249 0.02181 0.01500 -0.0715 0.0055 1.0000
8.750 1.2372 0.02285 0.01615 -0.0693 0.0053 1.0000
9.000 1.2477 0.02386 0.01726 -0.0667 0.0051 1.0000
9.250 1.2571 0.02498 0.01848 -0.0640 0.0049 1.0000
9.500 1.2659 0.02622 0.01984 -0.0615 0.0047 1.0000
9.750 1.2749 0.02751 0.02126 -0.0591 0.0045 1.0000
10.000 1.2841 0.02879 0.02264 -0.0569 0.0043 1.0000
10.250 1.2922 0.03030 0.02429 -0.0548 0.0042 1.0000
10.500 1.3003 0.03176 0.02586 -0.0528 0.0041 1.0000
10.750 1.3074 0.03334 0.02756 -0.0509 0.0040 1.0000
11.000 1.3134 0.03514 0.02950 -0.0491 0.0039 1.0000
11.250 1.3180 0.03706 0.03156 -0.0474 0.0038 1.0000
11.500 1.3210 0.03924 0.03389 -0.0458 0.0037 1.0000
11.750 1.3209 0.04194 0.03677 -0.0442 0.0036 1.0000
12.000 1.3178 0.04510 0.04014 -0.0427 0.0036 1.0000
12.250 1.3113 0.04874 0.04402 -0.0415 0.0035 1.0000
12.500 1.2984 0.05338 0.04894 -0.0406 0.0035 1.0000
12.750 1.2891 0.05750 0.05327 -0.0404 0.0034 1.0000
13.000 1.2794 0.06181 0.05780 -0.0406 0.0034 1.0000
13.250 1.2695 0.06635 0.06255 -0.0414 0.0034 1.0000
13.500 1.2540 0.07206 0.06847 -0.0430 0.0034 1.0000
13.750 1.2436 0.07722 0.07382 -0.0448 0.0033 1.0000
14.000 1.2243 0.08437 0.08117 -0.0479 0.0033 1.0000
14.250 1.2068 0.09166 0.08865 -0.0514 0.0033 1.0000
14.500 1.1879 0.09977 0.09695 -0.0558 0.0033 1.0000
14.750 1.1674 0.10881 0.10615 -0.0611 0.0034 1.0000
15.000 1.1480 0.11831 0.11581 -0.0668 0.0034 1.0000
15.250 1.1265 0.12898 0.12662 -0.0734 0.0034 1.0000
15.500 1.1062 0.14033 0.13810 -0.0804 0.0034 1.0000
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Polar data table (+)
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