HOBIESMO1.DAT (hobiesm-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: HOBIESMO1.DAT (hobiesm-il) Reynolds number: 200,000 Max Cl/Cd: 78.96 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hobiesm-il-200000-n5.txt Download as CSV file: xf-hobiesm-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3880 0.08697 0.08352 -0.0357 1.0000 0.0167
-8.750 -0.3921 0.08301 0.07962 -0.0368 1.0000 0.0167
-8.500 -0.3993 0.07905 0.07573 -0.0376 1.0000 0.0168
-8.250 -0.4107 0.07545 0.07223 -0.0376 1.0000 0.0167
-8.000 -0.4249 0.07179 0.06868 -0.0377 1.0000 0.0167
-7.750 -0.4390 0.06736 0.06435 -0.0391 1.0000 0.0166
-7.500 -0.4271 0.03128 0.02707 -0.0835 0.9810 0.0160
-7.250 -0.3982 0.02681 0.02195 -0.0878 0.9739 0.0171
-7.000 -0.3645 0.02434 0.01895 -0.0908 0.9696 0.0190
-6.750 -0.3350 0.02234 0.01650 -0.0923 0.9625 0.0201
-6.500 -0.3035 0.01966 0.01343 -0.0944 0.9577 0.0217
-6.250 -0.2724 0.01844 0.01202 -0.0956 0.9514 0.0234
-6.000 -0.2400 0.01756 0.01091 -0.0969 0.9453 0.0260
-5.750 -0.2072 0.01649 0.00961 -0.0981 0.9395 0.0276
-5.500 -0.1760 0.01564 0.00855 -0.0989 0.9322 0.0288
-5.250 -0.1437 0.01463 0.00742 -0.1001 0.9259 0.0313
-5.000 -0.1130 0.01402 0.00670 -0.1008 0.9180 0.0350
-4.750 -0.0814 0.01345 0.00597 -0.1015 0.9109 0.0386
-4.500 -0.0510 0.01285 0.00528 -0.1020 0.9028 0.0461
-4.250 -0.0215 0.01237 0.00482 -0.1023 0.8945 0.0658
-4.000 0.0087 0.01208 0.00451 -0.1028 0.8867 0.0881
-3.750 0.0369 0.01188 0.00425 -0.1027 0.8775 0.1028
-3.500 0.0656 0.01169 0.00403 -0.1029 0.8693 0.1208
-3.250 0.0935 0.01153 0.00388 -0.1028 0.8602 0.1411
-3.000 0.1210 0.01137 0.00368 -0.1027 0.8511 0.1558
-2.750 0.1490 0.01119 0.00347 -0.1026 0.8428 0.1684
-2.500 0.1760 0.01104 0.00327 -0.1023 0.8331 0.1817
-2.250 0.2033 0.01089 0.00312 -0.1021 0.8239 0.1986
-2.000 0.2307 0.01076 0.00298 -0.1019 0.8151 0.2196
-1.750 0.2575 0.01064 0.00288 -0.1016 0.8051 0.2427
-1.500 0.2845 0.01054 0.00279 -0.1013 0.7955 0.2666
-1.250 0.3116 0.01044 0.00272 -0.1010 0.7860 0.2939
-1.000 0.3383 0.01035 0.00267 -0.1007 0.7757 0.3235
-0.750 0.3650 0.01027 0.00263 -0.1004 0.7653 0.3535
-0.500 0.3917 0.01018 0.00259 -0.1000 0.7549 0.3855
-0.250 0.4181 0.01008 0.00257 -0.0996 0.7443 0.4249
0.000 0.4440 0.00993 0.00257 -0.0992 0.7329 0.4783
0.250 0.4689 0.00968 0.00260 -0.0985 0.7213 0.5695
0.750 0.5308 0.00889 0.00257 -0.0990 0.6973 1.0000
1.000 0.5574 0.00899 0.00258 -0.0986 0.6847 1.0000
1.250 0.5839 0.00910 0.00261 -0.0982 0.6716 1.0000
1.500 0.6103 0.00923 0.00266 -0.0978 0.6583 1.0000
1.750 0.6366 0.00936 0.00273 -0.0974 0.6446 1.0000
2.000 0.6629 0.00950 0.00280 -0.0970 0.6307 1.0000
2.250 0.6890 0.00965 0.00290 -0.0965 0.6166 1.0000
2.500 0.7151 0.00981 0.00303 -0.0961 0.6025 1.0000
2.750 0.7411 0.00998 0.00317 -0.0956 0.5882 1.0000
3.000 0.7670 0.01017 0.00332 -0.0952 0.5740 1.0000
3.250 0.7928 0.01036 0.00350 -0.0947 0.5597 1.0000
3.500 0.8184 0.01057 0.00371 -0.0942 0.5454 1.0000
3.750 0.8440 0.01078 0.00393 -0.0937 0.5310 1.0000
4.000 0.8694 0.01101 0.00417 -0.0932 0.5157 1.0000
4.250 0.8930 0.01131 0.00438 -0.0923 0.4875 1.0000
4.500 0.9152 0.01169 0.00465 -0.0912 0.4495 1.0000
4.750 0.9372 0.01211 0.00494 -0.0901 0.4095 1.0000
5.000 0.9570 0.01272 0.00530 -0.0888 0.3511 1.0000
5.250 0.9720 0.01382 0.00587 -0.0869 0.2532 1.0000
5.500 0.9741 0.01650 0.00728 -0.0836 0.0529 1.0000
5.750 0.9928 0.01749 0.00820 -0.0822 0.0314 1.0000
6.000 1.0126 0.01831 0.00914 -0.0809 0.0249 1.0000
6.250 1.0327 0.01908 0.01003 -0.0796 0.0210 1.0000
6.500 1.0518 0.01990 0.01098 -0.0782 0.0188 1.0000
6.750 1.0688 0.02087 0.01206 -0.0766 0.0172 1.0000
7.000 1.0809 0.02224 0.01353 -0.0743 0.0159 1.0000
7.250 1.0950 0.02338 0.01476 -0.0723 0.0147 1.0000
7.500 1.1107 0.02435 0.01583 -0.0706 0.0135 1.0000
7.750 1.1238 0.02559 0.01716 -0.0685 0.0127 1.0000
8.000 1.1367 0.02691 0.01860 -0.0664 0.0121 1.0000
8.250 1.1492 0.02829 0.02005 -0.0642 0.0115 1.0000
8.500 1.1625 0.02976 0.02160 -0.0623 0.0111 1.0000
8.750 1.1770 0.03139 0.02331 -0.0606 0.0107 1.0000
9.000 1.1931 0.03338 0.02538 -0.0594 0.0103 1.0000
9.250 1.2112 0.03599 0.02815 -0.0584 0.0096 1.0000
9.500 1.2241 0.03744 0.02985 -0.0565 0.0091 1.0000
9.750 1.2367 0.03942 0.03209 -0.0547 0.0086 1.0000
10.000 1.2475 0.04192 0.03487 -0.0528 0.0083 1.0000
10.250 1.2540 0.04459 0.03782 -0.0506 0.0082 1.0000
10.500 1.2563 0.04737 0.04093 -0.0482 0.0081 1.0000
10.750 1.2546 0.05035 0.04420 -0.0457 0.0080 1.0000
11.000 1.2495 0.05351 0.04764 -0.0434 0.0079 1.0000
11.250 1.2411 0.05696 0.05135 -0.0415 0.0078 1.0000
11.500 1.2308 0.06062 0.05527 -0.0400 0.0078 1.0000
11.750 1.2181 0.06467 0.05958 -0.0392 0.0078 1.0000
12.000 1.2041 0.06910 0.06423 -0.0390 0.0078 1.0000
12.250 1.1884 0.07403 0.06939 -0.0396 0.0079 1.0000
12.500 1.1717 0.07939 0.07497 -0.0410 0.0079 1.0000
12.750 1.1537 0.08538 0.08116 -0.0432 0.0079 1.0000
13.000 1.1352 0.09191 0.08789 -0.0463 0.0080 1.0000
13.250 1.1162 0.09910 0.09525 -0.0502 0.0080 1.0000
13.500 1.0973 0.10694 0.10325 -0.0549 0.0081 1.0000
13.750 1.0782 0.11565 0.11212 -0.0605 0.0082 1.0000
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Polar data table (+)
Polar graphs
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