HOBIE (hobie-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: HOBIE (hobie-il) Reynolds number: 500,000 Max Cl/Cd: 100.54 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hobie-il-500000.txt Download as CSV file: xf-hobie-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3825 0.08869 0.08637 -0.0313 1.0000 0.0298
-8.500 -0.3822 0.08569 0.08341 -0.0320 1.0000 0.0307
-8.250 -0.5811 0.02605 0.02263 -0.0719 0.9995 0.0216
-8.000 -0.5512 0.02046 0.01622 -0.0765 0.9965 0.0230
-7.750 -0.5132 0.02073 0.01656 -0.0787 0.9944 0.0239
-7.500 -0.4775 0.02065 0.01643 -0.0805 0.9913 0.0252
-7.250 -0.4428 0.01905 0.01447 -0.0827 0.9880 0.0271
-7.000 -0.4068 0.01770 0.01292 -0.0852 0.9853 0.0288
-6.750 -0.3672 0.01792 0.01316 -0.0876 0.9833 0.0302
-6.500 -0.3347 0.01735 0.01244 -0.0887 0.9780 0.0323
-6.250 -0.2993 0.01629 0.01114 -0.0906 0.9745 0.0348
-6.000 -0.2616 0.01627 0.01115 -0.0928 0.9721 0.0364
-5.750 -0.2234 0.01592 0.01074 -0.0950 0.9704 0.0388
-5.500 -0.1917 0.01584 0.01050 -0.0956 0.9637 0.0412
-5.250 -0.1580 0.01443 0.00899 -0.0973 0.9592 0.0441
-5.000 -0.1240 0.01403 0.00856 -0.0986 0.9540 0.0464
-4.750 -0.0929 0.01370 0.00814 -0.0991 0.9454 0.0492
-4.500 -0.0609 0.01353 0.00787 -0.0997 0.9365 0.0511
-4.250 -0.0308 0.01214 0.00633 -0.1003 0.9264 0.0538
-4.000 -0.0029 0.01159 0.00575 -0.1002 0.9124 0.0561
-3.750 0.0248 0.01116 0.00525 -0.1000 0.8981 0.0580
-3.500 0.0521 0.01082 0.00483 -0.0997 0.8839 0.0601
-3.250 0.0793 0.01050 0.00442 -0.0993 0.8697 0.0617
-3.000 0.1063 0.01023 0.00406 -0.0989 0.8556 0.0627
-2.750 0.1333 0.01010 0.00384 -0.0984 0.8415 0.0636
-2.500 0.1592 0.00949 0.00315 -0.0979 0.8278 0.0655
-2.250 0.1856 0.00917 0.00275 -0.0975 0.8144 0.0670
-2.000 0.2122 0.00895 0.00247 -0.0970 0.8008 0.0687
-1.750 0.2389 0.00879 0.00225 -0.0966 0.7878 0.0705
-1.500 0.2658 0.00866 0.00206 -0.0962 0.7759 0.0728
-1.250 0.2929 0.00856 0.00191 -0.0959 0.7641 0.0748
-1.000 0.3199 0.00848 0.00177 -0.0955 0.7525 0.0764
-0.750 0.3470 0.00842 0.00165 -0.0952 0.7410 0.0790
-0.500 0.3740 0.00834 0.00154 -0.0948 0.7295 0.0851
-0.250 0.4007 0.00807 0.00148 -0.0945 0.7179 0.1512
0.000 0.4272 0.00786 0.00152 -0.0943 0.7063 0.2465
0.250 0.4538 0.00771 0.00153 -0.0939 0.6943 0.2997
0.500 0.4803 0.00761 0.00156 -0.0936 0.6816 0.3713
0.750 0.5064 0.00747 0.00160 -0.0932 0.6678 0.4412
1.000 0.5309 0.00710 0.00169 -0.0926 0.6531 0.6106
1.250 0.5647 0.00631 0.00172 -0.0935 0.6349 1.0000
1.500 0.5907 0.00644 0.00174 -0.0929 0.6119 1.0000
1.750 0.6163 0.00660 0.00177 -0.0923 0.5866 1.0000
2.000 0.6419 0.00679 0.00183 -0.0917 0.5633 1.0000
2.250 0.6679 0.00697 0.00190 -0.0912 0.5431 1.0000
2.500 0.6938 0.00715 0.00200 -0.0907 0.5235 1.0000
2.750 0.7195 0.00736 0.00211 -0.0902 0.5034 1.0000
3.000 0.7451 0.00758 0.00222 -0.0897 0.4803 1.0000
3.250 0.7709 0.00778 0.00235 -0.0892 0.4611 1.0000
3.500 0.7967 0.00800 0.00250 -0.0887 0.4446 1.0000
3.750 0.8225 0.00821 0.00265 -0.0883 0.4299 1.0000
4.000 0.8478 0.00846 0.00283 -0.0878 0.4129 1.0000
4.250 0.8733 0.00870 0.00302 -0.0873 0.3939 1.0000
4.500 0.8988 0.00894 0.00319 -0.0868 0.3683 1.0000
4.750 0.9225 0.00934 0.00339 -0.0860 0.3221 1.0000
5.250 0.9654 0.01066 0.00415 -0.0840 0.2170 1.0000
5.500 0.9889 0.01112 0.00454 -0.0833 0.1981 1.0000
5.750 1.0120 0.01162 0.00490 -0.0825 0.1611 1.0000
6.000 1.0275 0.01296 0.00569 -0.0808 0.0694 1.0000
6.250 1.0491 0.01363 0.00633 -0.0797 0.0584 1.0000
6.500 1.0725 0.01406 0.00680 -0.0789 0.0528 1.0000
6.750 1.0932 0.01478 0.00754 -0.0777 0.0460 1.0000
7.000 1.1166 0.01517 0.00796 -0.0770 0.0416 1.0000
7.250 1.1360 0.01597 0.00877 -0.0756 0.0366 1.0000
7.500 1.1590 0.01637 0.00921 -0.0748 0.0340 1.0000
7.750 1.1805 0.01690 0.00975 -0.0738 0.0313 1.0000
8.000 1.1967 0.01791 0.01080 -0.0720 0.0287 1.0000
8.250 1.2182 0.01838 0.01134 -0.0709 0.0270 1.0000
8.500 1.2381 0.01896 0.01195 -0.0697 0.0253 1.0000
8.750 1.2551 0.01975 0.01277 -0.0681 0.0239 1.0000
9.000 1.2643 0.02121 0.01430 -0.0654 0.0225 1.0000
9.250 1.2812 0.02193 0.01511 -0.0637 0.0218 1.0000
9.500 1.2968 0.02271 0.01597 -0.0619 0.0208 1.0000
9.750 1.3102 0.02346 0.01677 -0.0598 0.0199 1.0000
10.000 1.3223 0.02424 0.01759 -0.0575 0.0191 1.0000
10.250 1.3305 0.02536 0.01875 -0.0549 0.0184 1.0000
10.500 1.3318 0.02757 0.02105 -0.0516 0.0176 1.0000
10.750 1.3434 0.02855 0.02214 -0.0496 0.0173 1.0000
11.000 1.3536 0.02976 0.02348 -0.0476 0.0169 1.0000
11.250 1.3631 0.03111 0.02495 -0.0456 0.0164 1.0000
11.500 1.3719 0.03257 0.02652 -0.0438 0.0159 1.0000
11.750 1.3801 0.03409 0.02814 -0.0420 0.0155 1.0000
12.000 1.3873 0.03559 0.02974 -0.0404 0.0151 1.0000
12.250 1.3936 0.03711 0.03133 -0.0389 0.0147 1.0000
12.500 1.3992 0.03878 0.03305 -0.0376 0.0143 1.0000
12.750 1.4022 0.04141 0.03578 -0.0362 0.0139 1.0000
13.000 1.4009 0.04487 0.03949 -0.0347 0.0135 1.0000
13.250 1.4008 0.04725 0.04205 -0.0337 0.0133 1.0000
13.500 1.3989 0.05010 0.04509 -0.0329 0.0132 1.0000
13.750 1.3942 0.05351 0.04872 -0.0324 0.0130 1.0000
14.000 1.3877 0.05722 0.05263 -0.0322 0.0129 1.0000
14.250 1.3785 0.06142 0.05704 -0.0325 0.0127 1.0000
14.500 1.3671 0.06612 0.06196 -0.0333 0.0126 1.0000
14.750 1.3531 0.07140 0.06746 -0.0347 0.0126 1.0000
15.000 1.3369 0.07736 0.07363 -0.0368 0.0125 1.0000
15.250 1.3185 0.08406 0.08054 -0.0396 0.0125 1.0000
15.500 1.2981 0.09159 0.08829 -0.0433 0.0125 1.0000
15.750 1.2759 0.09999 0.09690 -0.0479 0.0126 1.0000
16.000 1.2515 0.10939 0.10651 -0.0535 0.0126 1.0000
16.250 1.2262 0.11964 0.11694 -0.0599 0.0127 1.0000
16.500 1.1987 0.13124 0.12873 -0.0674 0.0129 1.0000
16.750 1.1681 0.14462 0.14227 -0.0762 0.0131 1.0000
17.000 1.1286 0.16208 0.15987 -0.0875 0.0135 1.0000
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