HOBIE (hobie-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: HOBIE (hobie-il) Reynolds number: 1,000,000 Max Cl/Cd: 115.08 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hobie-il-1000000.txt Download as CSV file: xf-hobie-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.3214 0.12048 0.11883 -0.0256 1.0000 0.0161
-11.750 -0.8235 0.04528 0.04332 -0.0668 1.0000 0.0111
-11.250 -0.8450 0.02478 0.02184 -0.0821 1.0000 0.0112
-11.000 -0.8335 0.02239 0.01923 -0.0817 1.0000 0.0116
-10.750 -0.8171 0.02101 0.01772 -0.0809 1.0000 0.0119
-10.500 -0.7990 0.01999 0.01658 -0.0800 1.0000 0.0122
-10.250 -0.7805 0.01899 0.01546 -0.0790 1.0000 0.0126
-10.000 -0.7557 0.01801 0.01435 -0.0793 0.9995 0.0130
-9.750 -0.7234 0.01704 0.01322 -0.0809 0.9981 0.0135
-9.500 -0.6902 0.01622 0.01226 -0.0826 0.9965 0.0139
-9.250 -0.6578 0.01476 0.01058 -0.0846 0.9949 0.0148
-9.000 -0.6249 0.01404 0.00980 -0.0861 0.9933 0.0157
-8.750 -0.5931 0.01352 0.00920 -0.0872 0.9910 0.0165
-8.500 -0.5602 0.01298 0.00856 -0.0884 0.9888 0.0174
-8.250 -0.5267 0.01224 0.00769 -0.0899 0.9868 0.0183
-8.000 -0.4923 0.01162 0.00703 -0.0916 0.9851 0.0198
-7.750 -0.4565 0.01125 0.00660 -0.0933 0.9837 0.0212
-7.500 -0.4253 0.01090 0.00619 -0.0940 0.9801 0.0223
-7.250 -0.3922 0.01048 0.00576 -0.0952 0.9767 0.0248
-7.000 -0.3571 0.01032 0.00559 -0.0967 0.9741 0.0267
-6.750 -0.3227 0.00999 0.00523 -0.0980 0.9715 0.0289
-6.500 -0.2916 0.01000 0.00527 -0.0985 0.9661 0.0307
-6.250 -0.2597 0.01003 0.00529 -0.0992 0.9600 0.0326
-6.000 -0.2273 0.01013 0.00536 -0.0999 0.9533 0.0337
-5.750 -0.1979 0.00973 0.00494 -0.1002 0.9432 0.0360
-5.500 -0.1688 0.00976 0.00494 -0.1003 0.9310 0.0373
-5.250 -0.1402 0.00979 0.00492 -0.1002 0.9157 0.0390
-5.000 -0.1125 0.00981 0.00485 -0.0999 0.8985 0.0404
-4.750 -0.0852 0.00989 0.00483 -0.0995 0.8805 0.0413
-4.500 -0.0599 0.00926 0.00408 -0.0990 0.8623 0.0433
-4.250 -0.0336 0.00906 0.00383 -0.0986 0.8444 0.0448
-4.000 -0.0070 0.00894 0.00363 -0.0981 0.8274 0.0461
-3.750 0.0197 0.00886 0.00347 -0.0978 0.8116 0.0477
-3.500 0.0464 0.00872 0.00326 -0.0974 0.7971 0.0490
-3.250 0.0734 0.00864 0.00311 -0.0970 0.7838 0.0502
-3.000 0.1005 0.00856 0.00295 -0.0967 0.7718 0.0510
-2.750 0.1276 0.00848 0.00281 -0.0964 0.7595 0.0514
-2.500 0.1542 0.00816 0.00241 -0.0961 0.7471 0.0525
-2.250 0.1810 0.00783 0.00202 -0.0958 0.7358 0.0541
-2.000 0.2081 0.00766 0.00179 -0.0955 0.7252 0.0555
-1.750 0.2353 0.00755 0.00163 -0.0952 0.7145 0.0569
-1.500 0.2629 0.00744 0.00149 -0.0950 0.7044 0.0582
-1.250 0.2903 0.00737 0.00138 -0.0948 0.6942 0.0597
-0.750 0.3452 0.00727 0.00120 -0.0944 0.6712 0.0621
-0.500 0.3726 0.00724 0.00112 -0.0941 0.6585 0.0630
-0.250 0.4000 0.00723 0.00107 -0.0939 0.6443 0.0637
0.000 0.4272 0.00721 0.00099 -0.0936 0.6280 0.0670
0.250 0.4541 0.00720 0.00094 -0.0933 0.6090 0.0733
0.500 0.4803 0.00696 0.00092 -0.0930 0.5885 0.1773
0.750 0.5062 0.00695 0.00098 -0.0926 0.5610 0.2447
1.000 0.5322 0.00703 0.00103 -0.0922 0.5319 0.2723
1.250 0.5584 0.00701 0.00112 -0.0919 0.5085 0.3436
1.500 0.5848 0.00706 0.00118 -0.0916 0.4876 0.3812
1.750 0.6109 0.00702 0.00127 -0.0912 0.4674 0.4565
2.000 0.6353 0.00673 0.00142 -0.0907 0.4486 0.6554
2.250 0.6669 0.00615 0.00155 -0.0914 0.4312 1.0000
2.500 0.6935 0.00632 0.00164 -0.0911 0.4174 1.0000
2.750 0.7201 0.00647 0.00173 -0.0908 0.4050 1.0000
3.000 0.7468 0.00662 0.00183 -0.0904 0.3939 1.0000
3.250 0.7735 0.00677 0.00193 -0.0901 0.3804 1.0000
3.500 0.7998 0.00695 0.00203 -0.0898 0.3555 1.0000
3.750 0.8243 0.00732 0.00219 -0.0892 0.3127 1.0000
4.000 0.8457 0.00803 0.00251 -0.0881 0.2336 1.0000
4.250 0.8705 0.00838 0.00276 -0.0876 0.2143 1.0000
4.500 0.8961 0.00863 0.00297 -0.0871 0.2037 1.0000
4.750 0.9216 0.00890 0.00318 -0.0867 0.1922 1.0000
5.000 0.9476 0.00911 0.00336 -0.0863 0.1794 1.0000
5.250 0.9681 0.00992 0.00376 -0.0852 0.0994 1.0000
5.500 0.9895 0.01063 0.00426 -0.0841 0.0624 1.0000
5.750 1.0146 0.01092 0.00455 -0.0836 0.0560 1.0000
6.000 1.0390 0.01127 0.00488 -0.0830 0.0502 1.0000
6.250 1.0639 0.01156 0.00518 -0.0824 0.0454 1.0000
6.500 1.0886 0.01187 0.00547 -0.0819 0.0402 1.0000
6.750 1.1129 0.01221 0.00580 -0.0812 0.0352 1.0000
7.000 1.1366 0.01259 0.00614 -0.0806 0.0305 1.0000
7.250 1.1605 0.01295 0.00652 -0.0799 0.0274 1.0000
7.500 1.1839 0.01334 0.00689 -0.0791 0.0245 1.0000
7.750 1.2062 0.01385 0.00742 -0.0782 0.0222 1.0000
8.000 1.2295 0.01421 0.00782 -0.0774 0.0209 1.0000
8.250 1.2520 0.01465 0.00826 -0.0766 0.0194 1.0000
8.500 1.2707 0.01544 0.00910 -0.0751 0.0176 1.0000
8.750 1.2936 0.01579 0.00948 -0.0743 0.0170 1.0000
9.000 1.3155 0.01621 0.00993 -0.0734 0.0161 1.0000
9.250 1.3363 0.01670 0.01047 -0.0724 0.0153 1.0000
9.500 1.3553 0.01733 0.01112 -0.0710 0.0145 1.0000
9.750 1.3679 0.01844 0.01232 -0.0687 0.0136 1.0000
10.000 1.3872 0.01894 0.01288 -0.0674 0.0132 1.0000
10.250 1.4050 0.01952 0.01352 -0.0659 0.0128 1.0000
10.500 1.4214 0.02015 0.01421 -0.0643 0.0123 1.0000
10.750 1.4361 0.02075 0.01486 -0.0623 0.0119 1.0000
11.000 1.4486 0.02138 0.01552 -0.0600 0.0115 1.0000
11.250 1.4591 0.02211 0.01630 -0.0574 0.0111 1.0000
11.500 1.4618 0.02333 0.01759 -0.0540 0.0106 1.0000
11.750 1.4581 0.02508 0.01947 -0.0501 0.0103 1.0000
12.000 1.4684 0.02597 0.02044 -0.0481 0.0102 1.0000
12.250 1.4776 0.02699 0.02154 -0.0461 0.0100 1.0000
12.500 1.4851 0.02818 0.02281 -0.0442 0.0098 1.0000
12.750 1.4912 0.02956 0.02428 -0.0424 0.0096 1.0000
13.000 1.4969 0.03104 0.02585 -0.0407 0.0094 1.0000
13.250 1.5028 0.03258 0.02748 -0.0393 0.0091 1.0000
13.500 1.5074 0.03432 0.02929 -0.0380 0.0089 1.0000
13.750 1.5097 0.03638 0.03145 -0.0368 0.0088 1.0000
14.000 1.5128 0.03845 0.03361 -0.0360 0.0086 1.0000
14.250 1.5148 0.04073 0.03598 -0.0353 0.0084 1.0000
14.500 1.5153 0.04329 0.03863 -0.0348 0.0083 1.0000
14.750 1.5130 0.04627 0.04170 -0.0345 0.0082 1.0000
15.000 1.5070 0.04984 0.04538 -0.0345 0.0080 1.0000
15.250 1.4969 0.05409 0.04977 -0.0348 0.0079 1.0000
15.500 1.4839 0.05897 0.05481 -0.0354 0.0078 1.0000
15.750 1.4682 0.06449 0.06052 -0.0366 0.0077 1.0000
16.000 1.4654 0.06845 0.06459 -0.0379 0.0076 1.0000
16.250 1.4596 0.07301 0.06928 -0.0395 0.0076 1.0000
16.500 1.4558 0.07743 0.07382 -0.0413 0.0075 1.0000
16.750 1.4480 0.08265 0.07917 -0.0435 0.0075 1.0000
17.000 1.4375 0.08853 0.08519 -0.0461 0.0074 1.0000
17.250 1.4288 0.09425 0.09104 -0.0489 0.0074 1.0000
17.500 1.4182 0.10047 0.09739 -0.0520 0.0073 1.0000
17.750 1.4049 0.10739 0.10446 -0.0556 0.0073 1.0000
18.000 1.3956 0.11371 0.11090 -0.0590 0.0072 1.0000
18.250 1.3802 0.12145 0.11879 -0.0634 0.0072 1.0000
18.500 1.3667 0.12904 0.12650 -0.0678 0.0071 1.0000
18.750 1.3496 0.13766 0.13527 -0.0730 0.0071 1.0000
19.000 1.3328 0.14648 0.14424 -0.0785 0.0071 1.0000
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Polar data table (+)
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