HOBIE (hobie-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: HOBIE (hobie-il) Reynolds number: 500,000 Max Cl/Cd: 92.98 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hobie-il-500000-n5.txt Download as CSV file: xf-hobie-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HOBIE
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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.4200 0.10526 0.10288 -0.0281 1.0000 0.0083
-10.500 -0.4249 0.09994 0.09759 -0.0299 1.0000 0.0084
-10.000 -0.6887 0.02776 0.02446 -0.0832 0.9967 0.0076
-9.750 -0.6608 0.02464 0.02105 -0.0871 0.9938 0.0079
-9.500 -0.6325 0.02260 0.01877 -0.0894 0.9906 0.0082
-9.250 -0.6026 0.02089 0.01683 -0.0915 0.9879 0.0086
-9.000 -0.5720 0.01948 0.01518 -0.0934 0.9855 0.0091
-8.750 -0.5433 0.01829 0.01377 -0.0945 0.9817 0.0096
-8.500 -0.5119 0.01704 0.01233 -0.0961 0.9786 0.0102
-8.250 -0.4804 0.01607 0.01123 -0.0975 0.9750 0.0109
-8.000 -0.4496 0.01523 0.01024 -0.0986 0.9704 0.0116
-7.750 -0.4167 0.01444 0.00928 -0.1001 0.9673 0.0124
-7.500 -0.3880 0.01370 0.00841 -0.1005 0.9611 0.0133
-7.250 -0.3558 0.01304 0.00766 -0.1017 0.9569 0.0148
-7.000 -0.3263 0.01250 0.00698 -0.1022 0.9500 0.0162
-6.750 -0.2945 0.01187 0.00629 -0.1032 0.9439 0.0186
-6.500 -0.2643 0.01141 0.00573 -0.1038 0.9345 0.0212
-6.250 -0.2337 0.01113 0.00548 -0.1043 0.9233 0.0263
-6.000 -0.2032 0.01106 0.00539 -0.1047 0.9105 0.0311
-5.750 -0.1735 0.01112 0.00539 -0.1049 0.8967 0.0357
-5.500 -0.1447 0.01113 0.00528 -0.1049 0.8835 0.0388
-5.250 -0.1164 0.01119 0.00523 -0.1047 0.8703 0.0400
-5.000 -0.0895 0.01086 0.00483 -0.1045 0.8565 0.0425
-4.750 -0.0623 0.01084 0.00472 -0.1043 0.8401 0.0447
-4.500 -0.0355 0.01077 0.00453 -0.1039 0.8232 0.0468
-4.250 -0.0087 0.01067 0.00431 -0.1036 0.8074 0.0487
-4.000 0.0181 0.01055 0.00408 -0.1032 0.7936 0.0502
-3.500 0.0716 0.01026 0.00358 -0.1025 0.7665 0.0518
-3.250 0.0984 0.01007 0.00329 -0.1022 0.7548 0.0521
-3.000 0.1253 0.00991 0.00305 -0.1019 0.7431 0.0525
-2.750 0.1522 0.00981 0.00287 -0.1016 0.7318 0.0528
-2.500 0.1789 0.00953 0.00251 -0.1014 0.7205 0.0537
-2.250 0.2058 0.00928 0.00220 -0.1011 0.7095 0.0551
-2.000 0.2327 0.00913 0.00198 -0.1008 0.6976 0.0566
-1.750 0.2596 0.00903 0.00181 -0.1005 0.6848 0.0581
-1.500 0.2867 0.00895 0.00168 -0.1003 0.6722 0.0597
-1.250 0.3139 0.00889 0.00157 -0.1001 0.6595 0.0611
-1.000 0.3410 0.00885 0.00147 -0.0998 0.6455 0.0623
-0.750 0.3679 0.00885 0.00139 -0.0995 0.6291 0.0635
-0.500 0.3946 0.00886 0.00133 -0.0992 0.6113 0.0645
-0.250 0.4213 0.00890 0.00128 -0.0988 0.5934 0.0654
0.000 0.4479 0.00894 0.00125 -0.0985 0.5751 0.0671
0.250 0.4745 0.00899 0.00124 -0.0982 0.5567 0.0708
0.500 0.5010 0.00904 0.00125 -0.0978 0.5387 0.0769
0.750 0.5271 0.00887 0.00128 -0.0976 0.5213 0.1670
1.000 0.5534 0.00886 0.00138 -0.0973 0.5041 0.2294
1.250 0.5798 0.00892 0.00144 -0.0970 0.4871 0.2511
1.500 0.6058 0.00901 0.00152 -0.0966 0.4654 0.2728
1.750 0.6312 0.00906 0.00165 -0.0963 0.4418 0.3471
2.000 0.6570 0.00908 0.00178 -0.0959 0.4264 0.4034
2.250 0.6829 0.00899 0.00192 -0.0956 0.4171 0.4944
2.500 0.7071 0.00871 0.00209 -0.0950 0.4085 0.6754
3.000 0.7645 0.00838 0.00234 -0.0952 0.3881 1.0000
3.250 0.7907 0.00856 0.00247 -0.0948 0.3702 1.0000
3.500 0.8164 0.00878 0.00261 -0.0944 0.3459 1.0000
3.750 0.8415 0.00907 0.00277 -0.0939 0.3193 1.0000
4.000 0.8663 0.00939 0.00298 -0.0934 0.2917 1.0000
4.250 0.8886 0.00998 0.00330 -0.0925 0.2346 1.0000
4.500 0.9130 0.01035 0.00358 -0.0919 0.2191 1.0000
4.750 0.9381 0.01064 0.00385 -0.0914 0.2111 1.0000
5.000 0.9628 0.01096 0.00415 -0.0909 0.1995 1.0000
5.250 0.9876 0.01127 0.00443 -0.0904 0.1868 1.0000
5.500 1.0123 0.01157 0.00470 -0.0899 0.1694 1.0000
5.750 1.0289 0.01276 0.00536 -0.0883 0.0738 1.0000
6.000 1.0519 0.01324 0.00579 -0.0875 0.0613 1.0000
6.250 1.0754 0.01364 0.00620 -0.0868 0.0538 1.0000
6.500 1.0990 0.01402 0.00660 -0.0862 0.0457 1.0000
6.750 1.1219 0.01447 0.00703 -0.0854 0.0359 1.0000
7.000 1.1440 0.01498 0.00749 -0.0845 0.0264 1.0000
7.250 1.1657 0.01552 0.00800 -0.0835 0.0208 1.0000
7.500 1.1874 0.01603 0.00854 -0.0826 0.0178 1.0000
7.750 1.2083 0.01661 0.00915 -0.0815 0.0156 1.0000
8.000 1.2293 0.01714 0.00973 -0.0805 0.0141 1.0000
8.250 1.2490 0.01777 0.01039 -0.0792 0.0128 1.0000
8.500 1.2685 0.01839 0.01107 -0.0780 0.0118 1.0000
8.750 1.2876 0.01899 0.01174 -0.0767 0.0108 1.0000
9.000 1.3054 0.01968 0.01247 -0.0752 0.0101 1.0000
9.250 1.3208 0.02050 0.01335 -0.0734 0.0095 1.0000
9.500 1.3366 0.02124 0.01419 -0.0717 0.0091 1.0000
9.750 1.3505 0.02199 0.01501 -0.0696 0.0086 1.0000
10.000 1.3623 0.02276 0.01585 -0.0672 0.0082 1.0000
10.250 1.3729 0.02359 0.01676 -0.0648 0.0078 1.0000
10.500 1.3798 0.02468 0.01790 -0.0621 0.0074 1.0000
10.750 1.3891 0.02565 0.01898 -0.0597 0.0071 1.0000
11.000 1.3961 0.02682 0.02026 -0.0573 0.0069 1.0000
11.250 1.4027 0.02808 0.02162 -0.0550 0.0067 1.0000
11.500 1.4085 0.02947 0.02311 -0.0529 0.0065 1.0000
11.750 1.4140 0.03095 0.02469 -0.0510 0.0063 1.0000
12.000 1.4192 0.03254 0.02637 -0.0493 0.0061 1.0000
12.250 1.4232 0.03431 0.02824 -0.0478 0.0060 1.0000
12.500 1.4266 0.03624 0.03027 -0.0465 0.0058 1.0000
12.750 1.4280 0.03847 0.03262 -0.0453 0.0057 1.0000
13.000 1.4265 0.04112 0.03537 -0.0443 0.0056 1.0000
13.250 1.4262 0.04378 0.03816 -0.0435 0.0055 1.0000
13.500 1.4270 0.04644 0.04097 -0.0430 0.0054 1.0000
13.750 1.4268 0.04930 0.04398 -0.0427 0.0053 1.0000
14.000 1.4244 0.05255 0.04739 -0.0426 0.0052 1.0000
14.250 1.4235 0.05574 0.05072 -0.0428 0.0050 1.0000
14.500 1.4198 0.05940 0.05453 -0.0432 0.0049 1.0000
14.750 1.4153 0.06334 0.05862 -0.0440 0.0048 1.0000
15.000 1.4104 0.06753 0.06295 -0.0450 0.0047 1.0000
15.250 1.4046 0.07200 0.06757 -0.0464 0.0047 1.0000
15.500 1.3980 0.07679 0.07250 -0.0480 0.0046 1.0000
15.750 1.3917 0.08172 0.07756 -0.0499 0.0045 1.0000
16.000 1.3826 0.08731 0.08330 -0.0522 0.0045 1.0000
16.250 1.3743 0.09292 0.08905 -0.0548 0.0044 1.0000
16.500 1.3641 0.09906 0.09534 -0.0576 0.0044 1.0000
16.750 1.3533 0.10546 0.10188 -0.0608 0.0044 1.0000
17.000 1.3416 0.11222 0.10879 -0.0642 0.0043 1.0000
17.250 1.3298 0.11924 0.11595 -0.0680 0.0043 1.0000
17.500 1.3154 0.12705 0.12393 -0.0723 0.0043 1.0000
17.750 1.3031 0.13463 0.13164 -0.0767 0.0043 1.0000
18.000 1.2883 0.14305 0.14022 -0.0817 0.0043 1.0000
18.250 1.2719 0.15227 0.14961 -0.0873 0.0043 1.0000
18.500 1.2544 0.16211 0.15960 -0.0934 0.0043 1.0000
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