HOBIE (hobie-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: HOBIE (hobie-il) Reynolds number: 100,000 Max Cl/Cd: 59.81 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hobie-il-100000.txt Download as CSV file: xf-hobie-il-100000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3770 0.11194 0.10662 -0.0253 1.0000 0.0866
-9.500 -0.3817 0.10995 0.10469 -0.0279 1.0000 0.0897
-9.250 -0.3991 0.10923 0.10411 -0.0324 1.0000 0.0909
-9.000 -0.3771 0.10303 0.09788 -0.0293 1.0000 0.0934
-8.750 -0.3650 0.10005 0.09490 -0.0281 1.0000 0.0980
-8.500 -0.3720 0.09822 0.09316 -0.0301 1.0000 0.1035
-8.250 -0.3928 0.09732 0.09243 -0.0328 1.0000 0.1047
-8.000 -0.3658 0.09192 0.08696 -0.0294 1.0000 0.1093
-7.750 -0.3639 0.08958 0.08467 -0.0288 1.0000 0.1140
-7.500 -0.3826 0.08836 0.08361 -0.0298 1.0000 0.1178
-7.250 -0.3991 0.08556 0.08096 -0.0366 1.0000 0.1198
-7.000 -0.3776 0.08227 0.07764 -0.0278 1.0000 0.1241
-6.750 -0.3795 0.08008 0.07552 -0.0281 1.0000 0.1300
-6.500 -0.3932 0.07682 0.07235 -0.0360 1.0000 0.1346
-6.250 -0.3834 0.07479 0.07038 -0.0278 1.0000 0.1390
-6.000 -0.3904 0.07165 0.06718 -0.0389 1.0000 0.1489
-5.750 -0.3868 0.06970 0.06538 -0.0289 1.0000 0.1522
-5.500 -0.3842 0.06660 0.06219 -0.0358 1.0000 0.1642
-5.250 -0.3826 0.06466 0.06037 -0.0293 1.0000 0.1670
-5.000 -0.3739 0.06152 0.05714 -0.0339 1.0000 0.1795
-4.750 -0.3703 0.05964 0.05533 -0.0294 1.0000 0.1833
-4.500 -0.3485 0.05716 0.05253 -0.0376 1.0000 0.2073
-4.250 -0.3459 0.05423 0.04978 -0.0328 1.0000 0.2102
-4.000 -0.2662 0.03388 0.02755 -0.0569 1.0000 0.1164
-3.750 -0.2390 0.03041 0.02355 -0.0585 1.0000 0.1151
-3.500 -0.2058 0.02734 0.01989 -0.0605 0.9984 0.1130
-3.250 -0.1585 0.02527 0.01718 -0.0646 0.9917 0.1168
-3.000 -0.1121 0.02370 0.01504 -0.0682 0.9847 0.1186
-2.750 -0.0716 0.02246 0.01372 -0.0711 0.9771 0.1240
-2.500 -0.0272 0.02156 0.01263 -0.0743 0.9709 0.1278
-2.250 0.0101 0.02089 0.01177 -0.0761 0.9622 0.1321
-2.000 0.0551 0.02018 0.01114 -0.0795 0.9562 0.1402
-1.750 0.0902 0.01967 0.01060 -0.0809 0.9461 0.1470
-1.500 0.1313 0.01911 0.01015 -0.0834 0.9384 0.1578
-1.250 0.1707 0.01861 0.00984 -0.0856 0.9296 0.1817
-1.000 0.2079 0.01782 0.00968 -0.0874 0.9207 0.3002
-0.750 0.2520 0.01718 0.00952 -0.0904 0.9134 0.4573
-0.500 0.2854 0.01631 0.00947 -0.0908 0.9033 0.6666
-0.250 0.3481 0.01540 0.00888 -0.0965 0.8977 1.0000
0.000 0.3855 0.01530 0.00860 -0.0978 0.8853 1.0000
0.250 0.4237 0.01514 0.00828 -0.0991 0.8731 1.0000
0.500 0.4614 0.01493 0.00794 -0.1001 0.8607 1.0000
0.750 0.4975 0.01472 0.00762 -0.1008 0.8483 1.0000
1.000 0.5317 0.01454 0.00736 -0.1011 0.8357 1.0000
1.250 0.5607 0.01453 0.00726 -0.1006 0.8212 1.0000
1.500 0.5890 0.01455 0.00721 -0.1000 0.8065 1.0000
1.750 0.6168 0.01460 0.00721 -0.0993 0.7915 1.0000
2.000 0.6442 0.01466 0.00721 -0.0986 0.7761 1.0000
2.250 0.6713 0.01475 0.00723 -0.0977 0.7603 1.0000
2.500 0.6980 0.01487 0.00729 -0.0969 0.7446 1.0000
2.750 0.7244 0.01503 0.00742 -0.0961 0.7290 1.0000
3.000 0.7499 0.01522 0.00759 -0.0952 0.7125 1.0000
3.250 0.7755 0.01543 0.00777 -0.0943 0.6965 1.0000
3.500 0.8012 0.01564 0.00799 -0.0935 0.6809 1.0000
3.750 0.8266 0.01584 0.00820 -0.0926 0.6650 1.0000
4.000 0.8514 0.01601 0.00837 -0.0915 0.6474 1.0000
4.250 0.8762 0.01613 0.00849 -0.0904 0.6290 1.0000
4.500 0.9011 0.01621 0.00857 -0.0893 0.6100 1.0000
4.750 0.9260 0.01635 0.00868 -0.0881 0.5912 1.0000
5.000 0.9496 0.01654 0.00893 -0.0870 0.5708 1.0000
5.250 0.9736 0.01671 0.00908 -0.0857 0.5490 1.0000
5.500 0.9962 0.01692 0.00932 -0.0843 0.5247 1.0000
5.750 1.0188 0.01717 0.00954 -0.0829 0.4999 1.0000
6.000 1.0396 0.01741 0.00979 -0.0812 0.4696 1.0000
6.250 1.0593 0.01771 0.01010 -0.0793 0.4354 1.0000
6.500 1.0767 0.01812 0.01043 -0.0772 0.3904 1.0000
6.750 1.0895 0.01876 0.01080 -0.0744 0.3055 1.0000
7.000 1.0914 0.02099 0.01206 -0.0706 0.1805 1.0000
7.250 1.1005 0.02291 0.01340 -0.0680 0.1164 1.0000
7.500 1.1108 0.02460 0.01496 -0.0654 0.1007 1.0000
7.750 1.1214 0.02625 0.01657 -0.0628 0.0911 1.0000
8.000 1.1326 0.02815 0.01834 -0.0604 0.0846 1.0000
8.250 1.1512 0.02980 0.02006 -0.0589 0.0788 1.0000
8.500 1.1730 0.03189 0.02201 -0.0581 0.0730 1.0000
8.750 1.2037 0.03461 0.02475 -0.0582 0.0696 1.0000
9.000 1.2273 0.03656 0.02695 -0.0573 0.0661 1.0000
9.250 1.2510 0.03886 0.02938 -0.0568 0.0625 1.0000
9.500 1.2762 0.04190 0.03256 -0.0564 0.0607 1.0000
9.750 1.2984 0.04568 0.03656 -0.0558 0.0596 1.0000
10.000 1.3139 0.05113 0.04236 -0.0550 0.0585 1.0000
10.250 1.3179 0.05292 0.04465 -0.0520 0.0576 1.0000
10.500 1.3212 0.05588 0.04806 -0.0493 0.0572 1.0000
10.750 1.3246 0.06014 0.05268 -0.0472 0.0575 1.0000
11.000 1.3338 0.06636 0.05915 -0.0464 0.0587 1.0000
11.250 1.3301 0.06730 0.06051 -0.0428 0.0597 1.0000
11.500 1.2929 0.06951 0.06332 -0.0370 0.0615 1.0000
11.750 1.2570 0.07341 0.06761 -0.0335 0.0631 1.0000
12.000 1.2265 0.07831 0.07281 -0.0325 0.0645 1.0000
12.250 1.1975 0.08400 0.07873 -0.0332 0.0657 1.0000
12.500 1.1689 0.09046 0.08538 -0.0354 0.0667 1.0000
12.750 1.1404 0.09788 0.09295 -0.0391 0.0678 1.0000
13.000 1.1210 0.10564 0.10080 -0.0425 0.0694 1.0000
13.250 0.8272 0.14218 0.13784 -0.0662 0.0931 1.0000
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Polar data table (+)
Polar graphs
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