HOBIESMO1.DAT (hobiesm-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: HOBIESMO1.DAT (hobiesm-il) Reynolds number: 500,000 Max Cl/Cd: 109.99 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hobiesm-il-500000.txt Download as CSV file: xf-hobiesm-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3754 0.08563 0.08346 -0.0373 1.0000 0.0235
-8.500 -0.3780 0.08206 0.07994 -0.0380 1.0000 0.0235
-8.250 -0.4056 0.07634 0.07432 -0.0379 1.0000 0.0245
-8.000 -0.4185 0.07396 0.07201 -0.0363 1.0000 0.0245
-7.750 -0.4268 0.07155 0.06965 -0.0358 0.9996 0.0248
-7.500 -0.4045 0.02688 0.02361 -0.0901 0.9837 0.0158
-7.250 -0.3732 0.02394 0.02012 -0.0933 0.9779 0.0169
-7.000 -0.3435 0.01910 0.01472 -0.0967 0.9734 0.0180
-6.750 -0.3080 0.01740 0.01279 -0.0991 0.9709 0.0191
-6.500 -0.2761 0.01600 0.01116 -0.1004 0.9656 0.0201
-6.250 -0.2432 0.01483 0.00980 -0.1018 0.9603 0.0214
-6.000 -0.2079 0.01409 0.00888 -0.1034 0.9564 0.0229
-5.750 -0.1785 0.01310 0.00770 -0.1038 0.9481 0.0238
-5.500 -0.1470 0.01156 0.00597 -0.1048 0.9422 0.0256
-5.250 -0.1189 0.01093 0.00525 -0.1049 0.9326 0.0275
-5.000 -0.0895 0.01048 0.00471 -0.1051 0.9242 0.0300
-4.750 -0.0610 0.01006 0.00417 -0.1051 0.9153 0.0318
-4.500 -0.0341 0.00953 0.00352 -0.1047 0.9055 0.0355
-4.250 -0.0065 0.00915 0.00308 -0.1045 0.8968 0.0435
-4.000 0.0200 0.00868 0.00279 -0.1043 0.8874 0.0894
-3.750 0.0472 0.00859 0.00265 -0.1040 0.8783 0.1056
-3.500 0.0745 0.00848 0.00250 -0.1038 0.8699 0.1172
-3.250 0.1015 0.00836 0.00236 -0.1035 0.8605 0.1274
-3.000 0.1286 0.00826 0.00223 -0.1032 0.8519 0.1396
-2.750 0.1558 0.00816 0.00211 -0.1029 0.8433 0.1540
-2.500 0.1827 0.00804 0.00201 -0.1027 0.8340 0.1709
-2.250 0.2099 0.00793 0.00191 -0.1024 0.8255 0.1913
-2.000 0.2368 0.00779 0.00181 -0.1022 0.8163 0.2158
-1.750 0.2638 0.00767 0.00174 -0.1019 0.8070 0.2439
-1.500 0.2909 0.00759 0.00168 -0.1017 0.7982 0.2732
-1.250 0.3179 0.00750 0.00164 -0.1014 0.7882 0.3029
-1.000 0.3449 0.00742 0.00161 -0.1011 0.7783 0.3345
-0.750 0.3718 0.00735 0.00158 -0.1009 0.7685 0.3663
-0.500 0.3986 0.00727 0.00156 -0.1006 0.7580 0.4005
-0.250 0.4253 0.00716 0.00155 -0.1003 0.7468 0.4425
0.000 0.4516 0.00701 0.00156 -0.0999 0.7356 0.5071
0.250 0.4759 0.00666 0.00161 -0.0992 0.7242 0.6485
0.500 0.5119 0.00594 0.00160 -0.1006 0.7123 1.0000
0.750 0.5386 0.00603 0.00160 -0.1002 0.6996 1.0000
1.000 0.5652 0.00612 0.00162 -0.0998 0.6863 1.0000
1.250 0.5918 0.00622 0.00164 -0.0995 0.6725 1.0000
1.500 0.6183 0.00632 0.00169 -0.0991 0.6584 1.0000
1.750 0.6448 0.00644 0.00174 -0.0987 0.6439 1.0000
2.000 0.6712 0.00657 0.00180 -0.0983 0.6293 1.0000
2.250 0.6975 0.00671 0.00188 -0.0980 0.6147 1.0000
2.500 0.7238 0.00685 0.00198 -0.0976 0.6000 1.0000
2.750 0.7500 0.00699 0.00208 -0.0972 0.5852 1.0000
3.000 0.7762 0.00715 0.00220 -0.0968 0.5708 1.0000
3.250 0.8023 0.00732 0.00233 -0.0964 0.5549 1.0000
3.500 0.8273 0.00753 0.00247 -0.0958 0.5306 1.0000
3.750 0.8524 0.00775 0.00262 -0.0952 0.5059 1.0000
4.000 0.8770 0.00801 0.00278 -0.0946 0.4777 1.0000
4.250 0.9012 0.00831 0.00297 -0.0939 0.4463 1.0000
4.500 0.9242 0.00873 0.00322 -0.0930 0.4015 1.0000
4.750 0.9449 0.00938 0.00355 -0.0919 0.3320 1.0000
5.000 0.9506 0.01171 0.00464 -0.0888 0.1120 1.0000
5.250 0.9654 0.01321 0.00573 -0.0867 0.0275 1.0000
5.500 0.9884 0.01374 0.00632 -0.0858 0.0236 1.0000
5.750 1.0078 0.01469 0.00737 -0.0843 0.0200 1.0000
6.000 1.0298 0.01526 0.00801 -0.0833 0.0184 1.0000
6.250 1.0506 0.01594 0.00876 -0.0821 0.0169 1.0000
6.500 1.0703 0.01672 0.00959 -0.0807 0.0157 1.0000
6.750 1.0879 0.01765 0.01057 -0.0790 0.0148 1.0000
7.000 1.1015 0.01899 0.01198 -0.0768 0.0141 1.0000
7.250 1.1114 0.02103 0.01411 -0.0740 0.0136 1.0000
7.500 1.1293 0.02236 0.01551 -0.0724 0.0131 1.0000
7.750 1.1499 0.02292 0.01616 -0.0712 0.0124 1.0000
8.000 1.1691 0.02419 0.01751 -0.0699 0.0119 1.0000
8.250 1.1894 0.02578 0.01920 -0.0687 0.0117 1.0000
8.500 1.2110 0.02767 0.02121 -0.0678 0.0115 1.0000
8.750 1.2335 0.03011 0.02383 -0.0669 0.0115 1.0000
9.000 1.2555 0.03387 0.02788 -0.0659 0.0120 1.0000
9.250 1.2243 0.03984 0.03497 -0.0597 0.0195 1.0000
9.500 1.2325 0.03817 0.03352 -0.0563 0.0185 1.0000
9.750 1.2375 0.04005 0.03563 -0.0535 0.0176 1.0000
10.000 1.2368 0.04285 0.03865 -0.0505 0.0170 1.0000
10.250 1.2293 0.04566 0.04166 -0.0469 0.0166 1.0000
10.500 1.2151 0.04823 0.04439 -0.0428 0.0162 1.0000
10.750 1.1983 0.05124 0.04757 -0.0394 0.0160 1.0000
11.000 1.1793 0.05480 0.05131 -0.0369 0.0159 1.0000
11.250 1.1586 0.05894 0.05562 -0.0351 0.0158 1.0000
11.500 1.1359 0.06383 0.06069 -0.0343 0.0158 1.0000
11.750 1.1120 0.06930 0.06633 -0.0344 0.0158 1.0000
12.000 1.0856 0.07563 0.07284 -0.0354 0.0159 1.0000
12.250 1.0568 0.08269 0.08008 -0.0376 0.0161 1.0000
12.500 1.0268 0.09024 0.08780 -0.0408 0.0163 1.0000
12.750 0.9946 0.09845 0.09617 -0.0452 0.0167 1.0000
13.000 0.9572 0.10677 0.10465 -0.0506 0.0173 1.0000
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Polar data table (+)
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