HOBIE (hobie-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: HOBIE (hobie-il) Reynolds number: 100,000 Max Cl/Cd: 60.3 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hobie-il-100000-n5.txt Download as CSV file: xf-hobie-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3656 0.09063 0.08566 -0.0342 1.0000 0.0338
-8.250 -0.3684 0.08744 0.08255 -0.0347 1.0000 0.0340
-8.000 -0.3735 0.08438 0.07957 -0.0348 1.0000 0.0341
-7.750 -0.3817 0.08152 0.07682 -0.0344 1.0000 0.0340
-7.500 -0.3890 0.07834 0.07374 -0.0347 1.0000 0.0339
-7.250 -0.3946 0.07484 0.07032 -0.0358 1.0000 0.0340
-7.000 -0.3995 0.07104 0.06659 -0.0374 1.0000 0.0340
-6.750 -0.4028 0.06686 0.06246 -0.0397 1.0000 0.0343
-6.500 -0.4033 0.06199 0.05760 -0.0431 1.0000 0.0351
-6.250 -0.3792 0.05052 0.04588 -0.0571 0.9952 0.0368
-6.000 -0.3395 0.03490 0.02881 -0.0741 0.9876 0.0397
-5.750 -0.3077 0.03328 0.02713 -0.0768 0.9817 0.0430
-5.500 -0.2720 0.03035 0.02370 -0.0804 0.9766 0.0476
-5.250 -0.2373 0.02720 0.01960 -0.0834 0.9700 0.0536
-5.000 -0.2043 0.02573 0.01804 -0.0854 0.9643 0.0586
-4.750 -0.1684 0.02424 0.01600 -0.0875 0.9582 0.0645
-4.500 -0.1355 0.02261 0.01417 -0.0891 0.9514 0.0696
-4.250 -0.0986 0.02152 0.01284 -0.0912 0.9458 0.0747
-4.000 -0.0647 0.02060 0.01163 -0.0924 0.9377 0.0788
-3.750 -0.0260 0.01969 0.01045 -0.0945 0.9323 0.0807
-3.500 0.0044 0.01870 0.00946 -0.0951 0.9231 0.0847
-3.250 0.0388 0.01800 0.00870 -0.0964 0.9161 0.0878
-3.000 0.0708 0.01740 0.00801 -0.0970 0.9072 0.0897
-2.750 0.1027 0.01689 0.00740 -0.0977 0.8982 0.0920
-2.500 0.1363 0.01642 0.00683 -0.0985 0.8899 0.0949
-2.250 0.1662 0.01601 0.00639 -0.0988 0.8798 0.0985
-2.000 0.1999 0.01561 0.00596 -0.0998 0.8727 0.1042
-1.750 0.2283 0.01534 0.00568 -0.0997 0.8623 0.1121
-1.500 0.2591 0.01498 0.00542 -0.1002 0.8538 0.1350
-1.250 0.2892 0.01458 0.00532 -0.1006 0.8445 0.2194
-1.000 0.3176 0.01434 0.00520 -0.1005 0.8336 0.2761
-0.750 0.3473 0.01411 0.00511 -0.1006 0.8229 0.3381
-0.500 0.3772 0.01392 0.00495 -0.1007 0.8118 0.3813
0.000 0.4307 0.01329 0.00489 -0.0998 0.7869 0.5554
0.500 0.4927 0.01240 0.00463 -0.0996 0.7600 1.0000
0.750 0.5199 0.01249 0.00457 -0.0992 0.7451 1.0000
1.000 0.5469 0.01259 0.00454 -0.0987 0.7304 1.0000
1.250 0.5739 0.01271 0.00454 -0.0982 0.7164 1.0000
1.500 0.6005 0.01284 0.00459 -0.0977 0.7024 1.0000
1.750 0.6269 0.01299 0.00467 -0.0972 0.6883 1.0000
2.000 0.6531 0.01314 0.00476 -0.0967 0.6739 1.0000
2.250 0.6792 0.01330 0.00488 -0.0962 0.6593 1.0000
2.500 0.7052 0.01346 0.00501 -0.0956 0.6441 1.0000
2.750 0.7311 0.01364 0.00515 -0.0950 0.6284 1.0000
3.000 0.7569 0.01382 0.00531 -0.0944 0.6129 1.0000
3.250 0.7825 0.01402 0.00548 -0.0938 0.5971 1.0000
3.500 0.8081 0.01423 0.00568 -0.0932 0.5816 1.0000
3.750 0.8337 0.01447 0.00591 -0.0926 0.5670 1.0000
4.000 0.8589 0.01472 0.00616 -0.0920 0.5517 1.0000
4.250 0.8836 0.01499 0.00642 -0.0912 0.5338 1.0000
4.500 0.9080 0.01528 0.00669 -0.0904 0.5153 1.0000
4.750 0.9322 0.01560 0.00700 -0.0896 0.4969 1.0000
5.000 0.9566 0.01592 0.00738 -0.0888 0.4808 1.0000
5.250 0.9805 0.01626 0.00777 -0.0880 0.4628 1.0000
5.500 1.0032 0.01664 0.00814 -0.0869 0.4401 1.0000
5.750 1.0255 0.01708 0.00857 -0.0858 0.4176 1.0000
6.000 1.0484 0.01750 0.00907 -0.0849 0.3980 1.0000
6.250 1.0700 0.01795 0.00959 -0.0838 0.3704 1.0000
6.500 1.0884 0.01854 0.01005 -0.0822 0.3195 1.0000
6.750 1.1029 0.01951 0.01068 -0.0802 0.2487 1.0000
7.000 1.1146 0.02093 0.01168 -0.0780 0.1997 1.0000
7.250 1.1237 0.02274 0.01288 -0.0758 0.0963 1.0000
7.500 1.1334 0.02450 0.01442 -0.0734 0.0709 1.0000
7.750 1.1451 0.02598 0.01595 -0.0712 0.0588 1.0000
8.000 1.1562 0.02741 0.01750 -0.0689 0.0506 1.0000
8.250 1.1667 0.02879 0.01900 -0.0666 0.0445 1.0000
8.500 1.1749 0.03029 0.02059 -0.0641 0.0403 1.0000
8.750 1.1837 0.03159 0.02205 -0.0615 0.0367 1.0000
9.000 1.1909 0.03303 0.02359 -0.0589 0.0340 1.0000
9.250 1.1972 0.03458 0.02521 -0.0565 0.0317 1.0000
9.500 1.2014 0.03663 0.02730 -0.0540 0.0296 1.0000
9.750 1.2128 0.03832 0.02916 -0.0522 0.0281 1.0000
10.000 1.2253 0.04020 0.03119 -0.0505 0.0267 1.0000
10.250 1.2369 0.04203 0.03316 -0.0490 0.0250 1.0000
10.500 1.2467 0.04388 0.03513 -0.0475 0.0236 1.0000
10.750 1.2555 0.04592 0.03726 -0.0461 0.0225 1.0000
11.000 1.2675 0.04860 0.04006 -0.0449 0.0216 1.0000
11.250 1.2791 0.05183 0.04351 -0.0438 0.0210 1.0000
11.500 1.2831 0.05463 0.04667 -0.0422 0.0205 1.0000
11.750 1.2828 0.05765 0.05001 -0.0407 0.0199 1.0000
12.000 1.2792 0.06086 0.05352 -0.0394 0.0194 1.0000
12.250 1.2731 0.06436 0.05730 -0.0385 0.0189 1.0000
12.500 1.2651 0.06812 0.06132 -0.0381 0.0185 1.0000
12.750 1.2548 0.07233 0.06578 -0.0381 0.0183 1.0000
13.000 1.2425 0.07696 0.07067 -0.0388 0.0181 1.0000
13.250 1.2276 0.08220 0.07617 -0.0401 0.0180 1.0000
13.500 1.2107 0.08805 0.08227 -0.0422 0.0180 1.0000
13.750 1.1917 0.09462 0.08908 -0.0451 0.0181 1.0000
14.000 1.1711 0.10194 0.09663 -0.0490 0.0182 1.0000
14.250 1.1489 0.11023 0.10513 -0.0540 0.0183 1.0000
14.500 1.1257 0.11962 0.11473 -0.0600 0.0186 1.0000
14.750 1.1011 0.13043 0.12570 -0.0672 0.0190 1.0000
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Polar data table (+)
Polar graphs
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