HOBIE (hobie-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: HOBIE (hobie-il) Reynolds number: 50,000 Max Cl/Cd: 40.78 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hobie-il-50000.txt Download as CSV file: xf-hobie-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3762 0.10275 0.09582 -0.0216 1.0000 0.2369
-7.750 -0.3517 0.09695 0.08999 -0.0202 1.0000 0.2459
-7.500 -0.3774 0.09767 0.09092 -0.0200 1.0000 0.2516
-7.250 -0.3567 0.09270 0.08593 -0.0186 1.0000 0.2638
-7.000 -0.3528 0.08963 0.08294 -0.0173 1.0000 0.2730
-6.750 -0.3763 0.08978 0.08331 -0.0168 1.0000 0.2812
-6.500 -0.3614 0.08563 0.07917 -0.0143 1.0000 0.2931
-6.250 -0.3603 0.08286 0.07647 -0.0129 1.0000 0.3023
-5.750 -0.3797 0.08013 0.07399 -0.0120 1.0000 0.3259
-5.500 -0.3718 0.07676 0.07068 -0.0086 1.0000 0.3390
-5.250 -0.3748 0.07465 0.06866 -0.0066 1.0000 0.3541
-4.750 -0.3807 0.07031 0.06449 -0.0023 1.0000 0.3874
-4.500 -0.3792 0.06776 0.06199 0.0010 1.0000 0.4045
-4.250 -0.3785 0.06542 0.05971 0.0039 1.0000 0.4222
-4.000 -0.3824 0.06369 0.05804 0.0059 1.0000 0.4488
-3.750 -0.3795 0.06121 0.05560 0.0107 1.0000 0.4729
-3.500 -0.2343 0.03994 0.03208 -0.0528 1.0000 0.1893
-3.250 -0.2066 0.03670 0.02842 -0.0550 1.0000 0.1868
-3.000 -0.1787 0.03413 0.02534 -0.0567 1.0000 0.1886
-2.750 -0.1504 0.03183 0.02256 -0.0579 1.0000 0.1882
-2.500 -0.1230 0.03008 0.02031 -0.0587 1.0000 0.1908
-2.250 -0.1002 0.02902 0.01912 -0.0586 1.0000 0.1975
-2.000 -0.0761 0.02802 0.01782 -0.0586 1.0000 0.2029
-1.750 -0.0516 0.02711 0.01657 -0.0585 1.0000 0.2083
-1.500 -0.0301 0.02651 0.01592 -0.0581 1.0000 0.2157
-1.250 -0.0088 0.02609 0.01542 -0.0576 1.0000 0.2291
-1.000 0.0136 0.02574 0.01498 -0.0573 1.0000 0.2470
-0.750 0.0376 0.02533 0.01460 -0.0573 1.0000 0.2729
-0.500 0.0630 0.02475 0.01439 -0.0574 1.0000 0.3492
-0.250 0.0866 0.02296 0.01430 -0.0562 1.0000 0.6525
0.000 0.1013 0.02264 0.01418 -0.0552 0.9988 1.0000
0.250 0.1564 0.02393 0.01492 -0.0616 0.9838 1.0000
0.500 0.2053 0.02501 0.01565 -0.0668 0.9681 1.0000
0.750 0.2510 0.02598 0.01636 -0.0713 0.9516 1.0000
1.000 0.2950 0.02688 0.01707 -0.0753 0.9352 1.0000
1.250 0.3376 0.02772 0.01777 -0.0788 0.9188 1.0000
1.500 0.3787 0.02851 0.01845 -0.0820 0.9026 1.0000
1.750 0.4182 0.02926 0.01912 -0.0847 0.8867 1.0000
2.000 0.4572 0.02995 0.01977 -0.0871 0.8708 1.0000
2.250 0.4969 0.03054 0.02033 -0.0894 0.8547 1.0000
2.500 0.5368 0.03104 0.02083 -0.0915 0.8387 1.0000
2.750 0.5770 0.03143 0.02126 -0.0934 0.8229 1.0000
3.000 0.6171 0.03172 0.02161 -0.0951 0.8073 1.0000
3.250 0.6563 0.03196 0.02194 -0.0964 0.7920 1.0000
3.500 0.6913 0.03224 0.02229 -0.0970 0.7768 1.0000
3.750 0.7258 0.03244 0.02258 -0.0973 0.7614 1.0000
4.000 0.7602 0.03254 0.02280 -0.0973 0.7459 1.0000
4.250 0.7915 0.03277 0.02317 -0.0969 0.7307 1.0000
4.500 0.8206 0.03314 0.02368 -0.0964 0.7156 1.0000
4.750 0.8505 0.03340 0.02409 -0.0957 0.7001 1.0000
5.000 0.8814 0.03353 0.02441 -0.0950 0.6843 1.0000
5.250 0.9131 0.03357 0.02463 -0.0941 0.6682 1.0000
5.500 0.9326 0.03426 0.02548 -0.0923 0.6481 1.0000
5.750 0.9728 0.03268 0.02409 -0.0903 0.6245 1.0000
6.000 1.0029 0.03166 0.02321 -0.0877 0.5976 1.0000
6.250 1.0337 0.03058 0.02225 -0.0851 0.5704 1.0000
6.500 1.0624 0.02950 0.02128 -0.0823 0.5400 1.0000
6.750 1.0887 0.02824 0.02000 -0.0789 0.5034 1.0000
7.000 1.1053 0.02739 0.01910 -0.0747 0.4569 1.0000
7.250 1.1117 0.02726 0.01885 -0.0696 0.3928 1.0000
7.500 1.1045 0.02832 0.01931 -0.0634 0.2872 1.0000
7.750 1.1006 0.03126 0.02117 -0.0589 0.2118 1.0000
8.000 1.1150 0.03402 0.02351 -0.0568 0.1744 1.0000
8.250 1.1325 0.03591 0.02539 -0.0551 0.1523 1.0000
8.500 1.1566 0.03791 0.02732 -0.0540 0.1382 1.0000
8.750 1.1818 0.04009 0.02951 -0.0532 0.1265 1.0000
9.000 1.2134 0.04299 0.03250 -0.0531 0.1190 1.0000
9.250 1.2386 0.04589 0.03561 -0.0524 0.1129 1.0000
9.500 1.2606 0.04939 0.03927 -0.0517 0.1080 1.0000
9.750 1.2735 0.05312 0.04354 -0.0499 0.1063 1.0000
10.000 1.2816 0.05722 0.04815 -0.0479 0.1057 1.0000
10.250 1.2828 0.06142 0.05283 -0.0457 0.1053 1.0000
10.500 1.2772 0.06568 0.05753 -0.0433 0.1050 1.0000
10.750 1.2660 0.07006 0.06228 -0.0409 0.1051 1.0000
11.000 1.2491 0.07442 0.06695 -0.0386 0.1056 1.0000
11.250 1.2278 0.07879 0.07156 -0.0364 0.1064 1.0000
11.500 1.2042 0.08367 0.07662 -0.0355 0.1073 1.0000
11.750 1.1822 0.08915 0.08226 -0.0357 0.1082 1.0000
12.000 1.1639 0.09519 0.08840 -0.0369 0.1091 1.0000
12.250 1.0448 0.11567 0.10906 -0.0537 0.1201 1.0000
12.500 1.0348 0.12421 0.11761 -0.0575 0.1230 1.0000
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Polar data table (+)
Polar graphs
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